text:
|Publication number
|Publication type
|Application number
|Publication date
|Apr 19, 1988
|Filing date
|Dec 23, 1985
|Priority date
|Dec 23, 1985
|Fee status
|Also published as
|Publication number
|Robert E. Field
|Original Assignee
|Field Robert E, United Technologies Corp
|Export Citation
|BiBTeX, EndNote, RefMan
|Patent Citations (41), Non-Patent Citations (5), Referenced by (84), Classifications (8), Legal Events (5)
|External Links: USPTO, USPTO Assignment, Espacenet
1. Technical Field
This invention relates to airfoils, and more particularly to film cooled airfoils.
2. Background Art
It is well known the external surface of airfoils may be cooled by conducting cooling air from an internal cavity to the external surface via a plurality of small passages. It is desired that the air exiting the passages remain entrained in the boundary layer on the surface of the airfoil for as long a distance as possible downstream of the passage to provide a protective film of cool air between the hot mainstream gas and the airfoil surface. The angle which the axis of the passage makes with the airfoil surface and its relation to the direction of hot gas flow over the airfoil surface at the passage breakout are important factors which influence film cooling effectiveness. Film cooling effectiveness is defined as the difference between the temperature of the main gas stream (Tg) and the temperature of the coolant film (Tf), divided by the temperature difference between the temperature of the main gas stream and the coolant temperature (Tc) at the passage exit (Tg-Tf)/(Tg-Tc). Film cooling effectiveness decreases rapidly with distance from the passage exit. Maintaining high film cooling effectiveness for as long a distance as possible over as large a surface area as possible is the main goal of airfoil film cooling.
It is well known in the art, that the engine airfoils must be cooled using a minimum amount of cooling air, since the cooling air is working fluid which has been extracted from the compressor and its loss from the gas flow path rapidly reduces engine efficiency. Airfoil designers are faced with the problem of cooling all the engine airfoils using a specified, maximum cooling fluid flow rate. The amount of fluid which flows through each individual cooling passage from an internal cavity into the gas path is controlled by the minimum cross-sectional area (metering area) of the cooling passage. The metering area is typically located where the passage intersects the internal cavity. The total of the metering areas for all the cooling passages and orifices leading from the airfoil controls the total flow rate of coolant from the airfoil, assuming internal and external pressures are fixed or at least beyond the designer's control. The designer has the job of specifying the passage size and the spacing between passages, as well as the shape and orientation of the passages, such that all areas of the airfoil are maintained below critical design temperature limits determined by the airfoil material capability, maximum stress, and life requirement considerations.
Ideally, it is desired to bathe 100% of the airfoil surface with a film of cooling air; however, the air leaving the passage exit generally forms a cooling film stripe no wider than or hardly wider than the dimension of the passage exit perpendicular to the gas flow. Limitations on the number, size, and spacing of cooling passages results in gaps in the protective film and/or areas of low film cooling effectiveness which may produce localized hot spots. Airfoil hot spots are one factor which limits the operating temperature of the engine.
U.S. Pat. No. 3,527,543 to Howald uses divergently tapered passages of circular cross section to increase the entrainment of coolant in the boundary layer from a given passage. The passages are also preferably oriented in a plane extending in the longitudinal direction or partially toward the gas flow direction to spread the coolant longitudinally upon its exit from the passage as it moves downstream. Despite these features, it has been determined by smoke flow visualization tests and engine hardware inspection that the longitudinal width of the coolant film from an eliptical passage breakout (i.e. Howald) continues to expand longitudinally only about a maximum of one passage exit minor diameter after the coolant is ejected on the airfoil surface. This fact, coupled with typical longitudinal spacing of three to six diameters between passages, result in areas of airfoil surface between and downstream of longitudinally spaced passages which receive no cooling fluid from that row of passages. Conical, angled passages as described in Howald U.S. Pat. No. 3,527,543 provide at best probably no more than 70% coverage (percentage of the distance between the centers of adjacent hole breakouts which is covered by coolant).
The velocity of the air leaving the cooling passage is dependent on the ratio of its pressure at the passage inlet to the pressure of the gas stream at the passage outlet. In general the higher the pressure ratio, the higher the exit velocity. Too high an exit velocity results in the cooling air penetrating into the gas stream and being carried away without providing effective film cooling. Too low a pressure ratio will result in gas stream ingestion into the cooling passage causing a complete loss of local airfoil cooling. Total loss of airfoil cooling usually has disastrous results, and because of this a margin of safety is usually maintained. This extra pressure for the safety margin drives the design toward the high pressure ratios. Tolerance of high pressure ratios is a desirable feature of film cooling designs. Diffusion of the cooling air flow by tapering the passage, as in the Howald patent discussed above is beneficial in providing this tolerance, but the narrow diffusion angles taught therein (12� maximum included angle) require long passages and, therefore, thick airfoil walls to obtain the reductions in exit velocities often deemed most desirable to reduce the sensitivity of the film cooling design to pressure ratio. The same limitation exists with respect to the trapezoidally shaped diffusion passages described in Sidenstick, U.S. Pat. No. 4,197,443. The maximum included diffusion angles taught therein in two mutually perpendicular planes are 7� and 14�, respectively, in order to assure that separation of the cooling fluid from the tapered walls does not occur and the cooling fluid entirely fills the passage as it exits into the hot gas stream. With such limits on the diffusing angles, only thicker airfoil walls and angling of the passages in the airfoil spanwise direction can produce wider passage outlets and smaller gaps between passages in the longitudinal direction. Wide diffusion angles would be preferred instead, but cannot be achieved using prior art teachings.
Japanese Patent No. 55-114806 shows, in its FIGS. 2 and 3 (reproduced herein as prior art FIGS. 18 and 19), a hollow airfoil having straight cylindrical passages disposed in a longitudinal row and emptying into a longitudinally extending slot formed in the external surface of the airfoil. While that patent appears to teach that the flow of cooling fluid from adjacent passages blends to form a film of cooling fluid of uniform thickness over the full length of the slot by the time the cooling fluid exits the slot and reaches the airfoil surface, our test experience indicates that the coolant fluid from the cylindrical passages moves downstream as a stripe of essentially constant width, which is substantially the diameter of the passage. Any diffusion which results in blending of adjacent stripes of coolant fluid occurs so far downstream that film cooling effectiveness at that point is well below what is required for most airfoil designs.
U.S. Pat. No. 3,515,499 to Beer et al describes an airfoil made from a stack of etched wafers. The finished airfoil includes several areas having a plurality of longitudinally spaced apart passages leading from an internal cavity to a common, longitudinally extending slot from which the cooling air is said to issue to form a film of cooling air over the airfoil external surface. In FIG. 1 thereof each passage appears to converge from its inlet to a minimum cross-sectional area where it intersects the slot. In the alternate embodiment of FIG. 9, the passage appears to have a small, constant size which exits into a considerably wider slot. Both configurations are likely to have the same drawbacks as discussed with respect to the Japanese patent; that is, the cooling fluid will not uniformly fill the slot before it enters the main gas stream, and considerably less than 100% film coverage downstream of the slot is likely.
Other publications relating to film cooling the external surface of an airfoil are: U.S. Pat. Nos. 2,149,510; 2,220,420; 2,489,683; and "Flight and Aircraft Engineer" No. 2460, Vol. 69, 3/16/56, pp. 292-295, all of which show the use of longitudinally extending slots for cooling either the leading edge or pressure and suction side airfoil surfaces. The slots shown therein extend completely through the airfoil wall to communicate directly with an internal cavity. Such slots are undesireable from a structural strength viewpoint; and they also require exceedingly large flow rates.
U.S. Pat. No. 4,303,374 shows a configuration for cooling the exposed, cut-back surface of the trailing edge of an airfoil. The configuration includes a plurality of longitudinally spaced apart, diverging passages within the trailing edge. Adjacent passages meet at their outlet ends to form a continuous film of cooling air over the cut-back surface.
A serial publication, "Advances in Heat Transfer" edited by T. F. Irvine, Jr. and J. P. Hartnett, Vol. 7, Academic Press (N.Y. 1971) includes a monograph titled Film Cooling, by Richard J. Goldstein, at pp. 321-379, which presents a survey of the art of film cooling. The survey shows elongated slots of different shapes extending entirely through the wall being cooled, and also passages of circular cross section extending through the wall.
One object of the present invention is an improved film cooling passage configuration for cooling a wall over which a hot gas stream is flowing.
Yet another object of the present invention is an airfoil film cooling passage which, in a short diffusing distance, is able to spread a small amount of coolant as a film over a large area of the external surface of the airfoil.
According to the present invention, a film cooling passage through a wall to be cooled has a metering section for directing a metered amount of coolant therethrough in a first direction, followed by a mixing section configured to create turbulence in the flow as it leaves the metering section and to at least partially disrupt its momentum in the first direction, followed by a diffusing section leading to the passage outlet at the outer surface of the wall over which a hot gas is to flow.
As discussed in the Background of the Invention, it has been a goal of the prior art to take a small amount of coolant fluid from the cool side of a wall to be cooled and to spread it out as a thin film over as large an area of the hot surface of the wall as possible. To do this, it is desirable to make the cooling passage outlet as long as possible in a direction perpendicular to the flow of hot gases over the surface at the passage outlet; and then the coolant fluid must uniformly (in the ideal case) fill the entire passage at the outlet so as to create a film of coolant downstream of the outlet which film is as wide as the outlet is long. The prior art teaches that diffusing the coolant flow from a small area inlet or metering section to a large area outlet necessitates the use of relatively small diffusion angles (i.e., less than 14�) to prevent separation from the diverging walls to assure that the coolant fluid fills the passage at the outlet. If one is limited to small diffusion angles, then long passage lengths are required to obtain large increases in passage outlet dimensions. When the wall to be cooled is thin, or has a concave curvature such as the wall of a hollow turbine airfoil, the length of the passage is severely limited.
In accordance with the present invention, it has been found, surprisingly, that a mixing section interconnecting the outlet of the metering section to the entrance of the diffusing section of the cooling passage permits the use of much larger diffusion angles in the diffusing section than has been possible using prior art configurations.
The mixing section may be of any configuration which creates turbulence in the coolant stream as it leaves the metering section, such as by rapidly expanding the flow to reduce and at least partially redirect the momentum of the stream such that the average velocity and cohesiveness of the coolant stream leaving the metering section outlet is diminished as it enters the diffusing section; and the mass flow of coolant no longer is uni-directional. This allows the coolant to more readily spread out within the diffusing section and to thereby stay attached to more widely diverging walls than was possible using prior art passage configurations. With the present invention a diffusing section having an included angle of 60� has been tested and becomes completely filled with coolant, which exits uniformly over the full extent of the outlet and forms a thin film of coolant on the hot surface. The use of angles of up to 80� are believed possible.
In a preferred embodiment of the present invention the mixing section is a step diffuser, wherein the coolant fluid exiting the metering section is suddenly expanded, such as by flowing over a step into a larger volume, as opposed to expanding by gradual diffusion. The sharp corner of the step is believed to create vortices which redirect part of the fluid momentum in a direction perpendicular to the original direction of flow from the metering section by the centrifugal forces created by the whirl of the vortex.
The foregoing and other objects, features and advantages of the present invention will become more apparent in the light of the following detailed description of preferred embodiments thereof as illustrated in the accompanying drawing.
FIG. 1 is a hollow turbine blade, partly broken away, which incorporates the features of the present invention.
FIG. 2 is a sectional view taken along the line 2--2 of FIG. 1.
FIG. 3 is an enlarged view of the circled portion of FIG. 2 designated by the letter A showing a cooling passage configured according to the present invention.
FIGS. 4(a), 4(b), and 4(c) are sectional views taken, respectively, along the lines 4(a)--4(a), 4(b)--4(b), and 4(c)--4(c) of FIG. 3.
FIG. 5 is a sectional view taken along the line 5--5 of FIG. 3.
FIG. 6 is a sectional view taken along the line 6--6 of FIG. 4(a).
FIG. 7 is a cross-sectional view, analogous to FIG. 4(a), showing an alternate configuration for the coolant passage of the present invention.
FIG. 8 is a sectional view taken along the line 8--8 of FIG. 7.
FIG. 9 is a perspective view of an electrode which can be used to simultaneously make a series of adjacent coolant passages similar to those described in FIGS. 3-6.
FIGS. 10-12 show the base line cooling passage configuration against which comparisons of the present invention may be made.
FIG. 13 is a graph which may be used to compare the film cooling effectiveness of a coolant passage configuration of the present invention to that of the base line configuration of FIGS. 10-12.
FIGS. 14 and 15 are schematic cross-sectional views, analogous to the view of FIG. 6, showing alternate configurations for coolant passages of the present invention.
FIGS. 16 and 17 are schematic cross-sectional views, analogous to the view of FIG. 3, showing alternate configurations for the coolant passages of the present invention.
FIGS. 18 and 19 are reproductions of FIGS. 2 and 3, respectively, of prior art Japanese Patent No. 55-114806.
As an exemplary embodiment of the present invention consider the turbine blade of FIG. 1 generally represented by the reference numeral 10. With reference to FIGS. 1 and 2, the blade 10 comprises a hollow airfoil 12 which extends in a spanwise or longitudinal direction from a root 14 which is integral therewith. A platform 16 is disposed at the base of the airfoil 12. The airfoil 12 comprises a wall 18 having an outer surface 20 and an inner surface 22. The inner surface 22 defines a longitudinally extending internal cavity which is divided into a plurality of adjacent longitudinally extending compartments 24, 26, 28 by longitudinally extending ribs 30, 32. A passage 34 within the root 14 communicates with the compartment 24; and a passage 36 within the root 14 communicates with both compartments 26 and 28. When the blade 10 is operating in its intended environment, such as in the turbine section of a gas turbine engine, coolant from a suitable source, such as compressor bleed air, is fed into the passages 34, 36 and pressurizes the compartments 24, 26 and 28.
As shown in FIG. 1, the airfoil 12 includes a plurality of longitudinally extending rows of coolant passages, such as the passages 38, 40 on the suction side; the passages 42 in the vicinity of the leading edge of the airfoil; and the passages 44 on the pressure side. Each passage 38, 40, 42, 44 extends from an inlet at the inner surface 22 of the airfoil to an outlet at the outer surface 20. These passages need not be identical within a row or from row to row. The airfoil shown in FIGS. 1 and 2 has been simplified for purposes of clarity, and the number of rows of passages, the number of passages in each row, and the spacing between rows, as shown in the drawing, is intended to be illustrative only and not limiting.
The coolant passages may be formed by any suitable means. A preferred method is by the well known technique of electro-discharge machining (EDM) using an electrode having the shape of the passage to be formed. A plurality of passages may be simultaneously formed using a "comb" electrode such as shown in FIG. 9, which is simply an electrode comprised of a plurality of adjacent "teeth" 45, each having the shape of the passage to be formed, and joined together at a common base 47. The method for forming the passages is not considered to be an aspect of the present invention.
Throughout the drawing the arrows 50 represent the direction of flow (i.e., steamlines) of hot gases over the surface of the airfoil. For purposes of the description of the present invention, the direction of flow of hot gases over either the pressure or suction side surfaces of the airfoil shall be considered the downstream direction. Thus, at any point on the suction or pressure side surface of the airfoil, the downstream direction is tangent to the surface of the airfoil and, except perhaps close to the airfoil tip or the airfoil base where atypical currents are generated, is substantially perpendicular to the spanwise direction of the airfoil.
The improved coolant passages of the present invention are herein shown as the passages 38 disposed in a spanwise row through the suction side wall of the airfoil, and shown greatly enlarged in FIGS. 3 through 6. Although described as suction side coolant passages, their use is not limited to the suction side of the airfoil. It will be evident that the present invention is useful for cooling any relatively thin wall which has a pressurized compartment or chamber containing relatively cool fluid on one side of the wall and a hot fluid flowing over the surface of the other side of the wall which, in the area to be cooled, is at a lower pressure than the coolant fluid.
Referring to FIGS. 3-6, the passage 38 includes, in series flow relation, a metering section 52, followed by a mixing section 54, followed by a diffusing section 56. In this embodiment, the metering section 52 is generally rectangular in cross-section; however, its specific cross-sectional shap is not critical to the present invention and may, for example, be circular or eliptical. By definition, the metering section 52 is that portion of the coolant passage 38 having the smallest cross-sectional area perpendicular to the direction of flow through the passage 38, which is along the passage centerline 39 which passes through the geometric center of the cross-sectional area of the metering section 52. The length B of the passage 38 is the length of the centerline 39 between the points where it intersects the surfaces 20, 22. In this specification, flow along the centerline 39 is in the "axial direction".
The metering section should have a constant cross-sectional area for no more than a distance equal to three times the effective diameter of the cross-sectional area of the metering section to reduce the cohesiveness of the mass of coolant exiting therefrom. The shorter the length the better, as long as the metering area is well defined. The inlet 58 to the metering section 52 communicates with the inlet 60 to the passage 38 at the inner surface 22 of the compartment 26 (FIG. 2) and receives a flow of coolant fluid therefrom. The outlet 62 of the metering section 52 is coincident with the inlet to the mixing section 54. In this exemplary embodiment, the mixing section comprises a step diffuser, as will be further described herein below.
The outlet 64 of the mixing section is coincident with the inlet of the diffusing section 56. The diffusing section 56 includes a pair of spaced apart flat surfaces 66, 68. The surface 68 is parallel to the spanwise or longitudinal direction of the airfoil. The surface 68 is also parallel to the centerline 39.
The surfaces 66, 68 intersect the outer surface 20 of the airfoil at angles γ1, γ2, respectively (FIG. 3). These angles are preferably shallow angles of no more than about 40� (most preferably 30� or less), in order to minimize penetration of the coolant stream into the hot gas stream in a direction perpendicular to the outer surface of the airfoil. Excessive penetration can result in the coolant being immediately swept away from the surface of the airfoil rather than forming a film of coolant entrained in the boundary layer of the airfoil surface downstream of the passage outlet. The intersection of the surfaces 66, 68 with the outer surface 20 define downstream and upstream edges 73, 75, respectively, of the passage outlet 71; and for this reason the surfaces 66, 68 are referred to as the downstream surface and upstream surface, respectively. Note that the downstream surface 66 faces generally upstream, and upstream surface 68, faces generally downstream. It is preferred that the downstream surface 66 diverges from the centerline 39 toward the passage outlet 71. Preferably, the downstream surface diverges by an angle from the upstream surface 68 by an angle of between 5� and 10�. This reduces the angle γ1, which is desirable. Although not preferred, the surfaces 66, 68 may be parallel to each other; and such a configuration is intended to fall within the scope of the present invention.
As best shown in FIGS. 4-6, the diffusing section 56 includes side surfaces 70, 72 which face each other and extend between the surfaces 66, 68. Each side surface also extends from the mixing section outlet to the passage outlet along a straight path which diverges from the axial direction 39 by an angle β (FIG. 6). Divergence angles β of up to 30� have been tested successfully, wherein a coolant film was produced having a width substantially equivalent to the full width of the passage outlet, meaning that the passage flowed "full". It is believed that with fine tuning divergence angles of up to 40� may be used.
As shown schematically in FIGS. 14 and 15, respectively, the side surfaces may also be convexly curved (70', 72') or be comprised of a plurality of straight sections (70" or 72"), each diverging from the axial direction by a greater angle than the preceding section. The effective angle of divergence in each case is β' and β", respectively.
Referring to FIGS. 4a through 4c, each side surface 70, 72 blends (as at 74, 76) along its length with the downstream surface 66 as a smooth curve, as opposed to a sharp corner or filet radius (see FIGS. 10-12 discussed below). Preferably the diameter of the curved corner at the outlet of the passage 38 (FIG. 4a) is on the order of the distance between the surfaces 66, 68 at the outlet. The diameter is reduced gradually as the passage tapers down toward the diffusing section inlet. The corners preferably form segments of an oblique cone along the length of the diffusing section. The apex of the cones are preferably located at points C (FIGS. 3 and 4(a)). The smoothly curved corners create counterrotating vortices which further aid in uniformly filling the diffusing section with coolant, enabling the use of larger divergence angles β than would otherwise be possible with the normal filet radii or sharp corners used by the prior art. This aspect of the present invention is further described and claimed in commonly owned, co-pending application U.S. Ser. No. 812,104, now a U.S. Pat. No. 4,684,323, titled "Improved Film Cooling Passages with Curved Corners" by the same inventor as the present application and filed on even date herewith. Such application is incorporated herein by reference.
The primary feature of the present invention is the mixing section 54 of the passage 38. The function of the mixing section 54 is to reduce and redirect the momentum of the coolant stream as it exits the metering section 52 before it reaches the diffusing section 56. In prior art passages such as shown in FIGS. 10-12 the coolant stream tends to remain a relatively cohesive, unidirectional mass which is difficult to redirect along the diverging surfaces 110, 112 of the diffusing section simply by viscous forces within the boundary layers. In accordance with the present invention, the redirection and reduction of the momentum of the coolant stream is brought about by increasing the cross-sectional area of the passage substantially step-wise, upstream of the diffusing section inlet, in a direction generally away from (i.e., opposite) the downstream direction 50 of the mainstream flow. In the embodiment of FIG. 3 this is toward and generally perpendicular to the plane of the upstream surface 68.
More specifically, in the embodiment of FIG. 3 the passage 38 has a step 90 at the metering section outlet 62. The step is perpendicular to the surface 68. The step 90 has a sharp corner or edge 92 which is believed to generate vortices along its length which gives a portion of the coolant fluid a component of velocity in a direction parallel to the edge 92. Alternate configurations for the step 90 are shown in FIG. 16. In FIG. 16(a) the step 90 is an undercut. In FIG. 16(b) the sharp inside corner or filet radius is replaced with a larger radius. In FIG. 16(c) the step 90 slopes toward the passage outlet, but at a sufficiently small angle that the flow from the metering section does not remain attached to the surface of the step downstream of the edge 92. Vortices are thus generated along the edge as in the embodiments of FIGS. 16(a) and (b). The slope of the step 90 must be selected such that the change in cross-sectional area at the metering section exit is rapid enough to generate the turbulence necessary to produce the desired results in the diffusing section 56 of the passage.
Preferably the passage cross-sectional area should increase suddenly at the metering section outlet to at least 1.5 times the metering section cross-sectional area. Also, the distance from the metering section outlet 62 to the upstream edge 75 of the passage outlet is preferably no greater than four times the equivalent diameter of the metering section cross-sectional area because the diffusing effects created by the vortices in the mixing section 54 decay rapidly, and the coolant flow tends to return to a cohesive state if the distance between the mixing section outlet 64 and the airfoil surface 20 becomes too large. Furthermore, the distance between the step and the inlet to the diffusing section also should not be so long as to allow the flow to re-coalesce with its momentum once again directed substantially only axially. Long mixing sections may, therefore, require a second step 93 or sudden further increase in cross-sectional area, as shown in FIG. 17.
Although the mixing section feature of the cooling passage of exemplary embodiment of FIGS. 3-6 is combined with the feature of a large curvature joining the side surfaces with the downstream surface in the diffusing section, these features provide benefits independent of each other; and the present invention is not limited to the combination of the two. Thus, the use of the mixing section with a diffusing section having standard filet radii (i.e., sharp corners), as shown in FIGS. 7 and 8, also provides significant improvements over the prior art. FIGS. 7 and 8 are views corresponding, respectively, to FIG. 4(a) and FIG. 6, which show an alternate configuration for the diffusing section 56 of FIG. 3 wherein the corners are all "sharp". The graph of FIG. 13 shows tests results for such alternate configuration as well as for a "baseline" configuration described below.
In FIG. 13 the horizontal axis is a dimensionless parameter P whose value is the ratio of the distance � from the outlet of the cooling passage (in the direction of the mainstream gas flow over the outlet) to a number directly related to the mass flow rate of cooling air exiting the passage. The vertical axis is a measure of the film cooling effectiveness E (as hereinabove defined) measured at a distance � downstream of the passage outlet. The maximum possible cooling effectiveness is 1.0. Because P is directly related to distance from the passage outlet, and since the distance downstream of the outlet is the only variable in these tests, P may be considered as a measure of distance downstream of the passage outlet.
The curve labeled A is for the baseline coolant passage as shown in FIGS. 10-12. The baseline configuration is used for comparison purposes and is similar to the coolant passages described in Sidenstick, U.S. Pat. No. 4,197,443 except the divergence angles are 10�. The baseline test piece was a flat plate having a thickness of 1.4 inch. A baseline passage was machined into the plate. The flow of hot gas over the passage outlet was perpendicular to the downstream edge of the passage outlet. The constant cross-section metering section of the passage had a length L of 0.475 inch; a width W of 0.450 inch; and a height H of 0.300 inch. The diffusing section 102 of each passage had an upstream surface 104 parallel to the axial direction 106 of the passage. The corners of the diffusing section 102 were all "sharp". The diffusing section 102 also had a downstream surface 108 which diverged at an angle of 10� from the axial direction. The side surfaces 110, 112 each diverged from the axial direction at an angle of 10� which we determined avoids separation (i.e., such that the passage flows "full" and produces a coolant film of substantially the same width as the passage outlet) despite the teaching of Sidenstick which suggests maximum divergence angles of 7�. The angle between the axial direction and the outer surface 114 of the test piece was 35�.
The curve B represents data for a single coolant passage according to the present invention and shaped as shown in FIGS. 7 and 8, which passage, in cross-section taken along the line A--A, appears the same as in the view shown in FIG. 3. The thickness of the flat plate test piece was 0.9 inch. The angle γ was 30� and θ was 10�. The angles β were 30�. The metering section had a length of 0.5 inch, a width W of 0.41 inch, and a height H of 0.28 inch. The mixing section had a length of 0.5 inch in the axial direction, a width of 0.41 inch and height of 0.42 inch. The mass flow rate of coolant through the passages represented by curves A and B was the same and constant during the test. The passages flowed "full" as evidenced by smoke flow visualization tests.
The graph shows that at 20 units distance downstream of the passage outlet the film cooling effectiveness of the present invention is about 0.05 greater than that of the baseline configuration; and at 40 units distance the difference is about 0.03. To put this in perspective, assuming a coolant temperature at the passage outlet of 1200� F. and a mainstream gas temperature of 2600� F., a 0.02 increase in cooling effectiveness translates into about a 28� F. decrease in the temperature of the coolant film for the same mass flow rate of coolant.
In addition to better cooling effectiveness directly downstream of each passage outlet, the wider divergence angles of the passages of the present invention result in spreading the same amount of coolant over a significantly greater area than the baseline configuration using the same metering section cross-sectional area and a passage length on the order of about half the length required by the baseline configuration. This permits the use of coolant passages with small ratios of length (B) to metering section effective diameter (D), which is particularly advantageous when the wall to be cooled is very thin.
In small airfoils with thin walls (e.g., 0.03 inch thick), where the sum of the cross-sectional area of the metering sections of all the coolant passages is restricted, and the minimum size of each metering section is limited by practical considerations to about 0.015 inch diameter, the present invention permits the passage outlets of a spanwise row of passages to be more closely spaced from one another than if prior art passages were used. Thus, over the same spanwise length of the airfoil, even the best shaped passages of the prior art provide considerably less coverage than passages of the present invention, for the same total mass flow rate of coolant.
In the embodiment hereinabove described, and as clearly shown in FIG. 1, each passage 38 of a spanwise row of passages 38 breaks out at the surface 20 of the airfoil to form an outlet completely separate from each of the other outlets. The present invention contemplates that adjacent passages may be sufficiently close together and formed in such a manner that the passages (more specifically, the side walls) intersect each other below the surface 20, whereby a continuous outlet slot is formed at the surface 20 which runs the length of the row of passages. During operation this slot becomes filled with coolant; and the film of coolant formed on the surface 20 downstream of the slot is continuous in the longitudinal direction over the length of the row, eliminating gaps in film coverage resulting from the gaps between passage outlets. This is more fully described and claimed in commonly owned, copending patent application Ser. No. 812,103, now a U.S. Pat. No. 4,664,597, titled "Improved Film Cooling Slots for Airfoils" by Thomas A. Auxier, Edward C. Hill, and Leon R. Anderson filed on even date herewith.
Although the invention has been shown and described with respect to a preferred embodiment thereof, it should be understood by those skilled in the art that other various changes and omissions in the form and detail of the invention may be made without departing from the spirit and scope thereof.
|Cited Patent
|Filing date
|Publication date
|Apr 8, 1929
|May 10, 1932
|Axel Holmstrom
|Propeller or turbine for water, air, and gases
|Jan 17, 1935
|Mar 7, 1939
|Cem Comp Electro Mec
|Method and means for preventing deterioration of turbo-machines
|Feb 9, 1939
|Nov 5, 1940
|Bbc Brown Boveri & Cie
|Means for cooling machine parts
|Jul 21, 1939
|Mar 25, 1941
|Bbc Brown Boveri & Cie
|Turbine blade
|Jul 25, 1946
|Aug 2, 1949
|Westinghouse Electric Corp
|Combustion chamber construction
|Nov 19, 1943
|Nov 29, 1949
|Edward A Stalker
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|Saint Gobain
|Process and apparatus for producing perforations of very small cross-section
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|Hitachi Ltd
|Ultra-high temperature burners
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|Wall element for combustion chambers
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|Blades and blade assemblies for turbine engines,compressors and the like
|Aug 26, 1965
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|Gen Electric
|Cooling of structural members particularly for gas turbine engines
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|Nov 24, 1970
|Gen Electric
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|Aerojet General Co
|Cooling passages wafer blade assemblies for turbine engines, compressors and the like
|Jun 29, 1972
|Mar 26, 1974
|Rolls Royce
|Cooled vane or blade for a gas turbine engine
|Aug 25, 1972
|Apr 2, 1974
|Rolls Royce
|Fluid flow blades
|Dec 15, 1972
|Aug 20, 1974
|Us Navy
|Dual purpose circulation control airfoil
|Jul 5, 1973
|Oct 29, 1974
|Gen Electric
|Blunted leading edge fan blade for noise reduction
|Mar 4, 1974
|Jun 17, 1975
|Boeing Co
|Airfoil leading edge structure with boundary layer control
|Jul 2, 1973
|Oct 28, 1975
|Supramar Ag
|Hydrofoil with lift control by airfreed for watercraft
|May 21, 1975
|Dec 7, 1976
|General Electric Company
|Combustor liner structure
|Oct 14, 1975
|Apr 12, 1977
|United Technologies Corporation
|Turbomachinery vane or blade with cooled platforms
|Sep 2, 1977
|Mar 6, 1979
|General Electric Company
|Tip cooling for turbine blades
|Apr 1, 1975
|Jul 24, 1979
|Rolls-Royce Limited
|Cooled blade for a gas turbine engine
|Jan 28, 1977
|Sep 25, 1979
|Rolls-Royce Limited
|Blade or vane for a gas turbine engine
|Sep 19, 1977
|Apr 8, 1980
|General Electric Company
|Method and apparatus for forming diffused cooling holes in an airfoil
|Nov 15, 1978
|Jul 29, 1980
|Tamura Raymond M
|Pollution reducing aircraft propulsion
|May 1, 1979
|May 19, 1981
|Bbc Brown, Boveri & Co., Ltd.
|Cooling-air nozzle for use in a heated chamber
|Feb 5, 1979
|Jun 2, 1981
|The Garrett Corporation
|Laminated airfoil
|Dec 15, 1978
|Dec 1, 1981
|General Electric Company
|Film cooled airfoil body
|Jun 11, 1979
|Feb 9, 1982
|Rice Ivan G
|Steam-cooled blading with steam thermal barrier for reheat gas turbine combined with steam turbine
|Oct 27, 1980
|May 24, 1983
|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
|Curved film cooling admission tube
|Jun 14, 1960
|Robert Pouit
|Turbines and in particular gas turbines
|Sep 15, 1978
|Mar 29, 1979
|Gen Electric
|Verfahren und vorrichtung zum ausbilden von diffusorfoermigen kuehlloechern in einem stromlinienfoermigen koerper
|Title not available
|Title not available
|Title not available
|Advances in Heat Transfer by Richard J. Goldstein, vol. 7, Academic Press, (N.Y.) (9/1971), the Monograph Film Cooling, pp. 321 379.
|Advances in Heat Transfer by Richard J. Goldstein, vol. 7, Academic Press, (N.Y.) (9/1971), the Monograph Film Cooling, pp. 321-379.
|Flight and Aircraft Engineer, No. 2460, vol. 69, 3 16 56, pp. 292 295.
|Flight and Aircraft Engineer, No. 2460, vol. 69, 3-16-56, pp. 292-295.
|NASA Technical Paper 1546, Influence of Coolant Tube Curvature of Film Cooling Effectiveness as Detected by Infrared Imagery by S. Stephen Papell et al., 9/1979.
|Citing Patent
|Filing date
|Publication date
|Oct 10, 1989
|Feb 12, 1991
|Rolls-Royce Plc
|Film cooled components
|Nov 28, 1990
|Mar 9, 1993
|The United States Of America As Represented By The Secretary Of The Air Force
|Turbine engine foil cap
|May 30, 1991
|Jun 29, 1993
|Rolls-Royce Plc
|Perforated two layered sheet for use in film cooling
|Jul 13, 1990
|Jan 25, 1994
|General Electric Company
|Curved film cooling holes for gas turbine engine vanes
|Oct 15, 1993
|Jan 17, 1995
|United Technologies Corporation
|High coverage shaped diffuser film hole for thin walls
|Feb 10, 1992
|Feb 28, 1995
|United Technologies Corporation
|Method of manufacturing an air cooled vane with film cooling pocket construction
|Jan 25, 1993
|May 30, 1995
|General Electric Company
|Film cooled wall
|Oct 29, 1992
|Jul 29, 1997
|General Electric Company
|Film cooled wall
|Jul 23, 1993
|Aug 26, 1997
|General Electric Company
|Film cooled slotted wall
|Aug 25, 1992
|Nov 25, 1997
|General Electric Company
|Turbine blade having transpiration strip cooling and method of manufacture
|Dec 17, 1997
|Apr 18, 2000
|United Technologies Corporation
|Apparatus and method for cooling an airfoil for a gas turbine engine
|May 23, 1997
|Jul 25, 2000
|Kabushiki Kaisha Toshiba
|Cooling system for a main body used in a gas stream
|Jul 6, 1998
|Aug 8, 2000
|United Technologies Corporation
|Coolable airfoil for a gas turbine engine
|Nov 3, 1999
|Jul 3, 2001
|General Electric Company
|Striated cooling hole
|Sep 17, 2003
|Mar 7, 2006
|General Electric Company
|Teardrop film cooled blade
|Aug 23, 2001
|Apr 17, 2007
|United Technologies Corporation
|Method for repairing an apertured gas turbine component
|Jan 27, 2004
|May 29, 2007
|Honeywell International, Inc.
|Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
|Oct 6, 2004
|Jul 24, 2007
|General Electric Company
|Stepped outlet turbine airfoil
|Aug 31, 2005
|Jul 31, 2007
|General Electric Company
|Pattern cooled turbine airfoil
|Oct 4, 2004
|Nov 27, 2007
|Alstom Technology Ltd
|Gas turbine airfoil leading edge cooling construction
|Jun 23, 2004
|Feb 12, 2008
|General Electric Company
|Chevron film cooled wall
|Dec 2, 2005
|Apr 1, 2008
|Siemens Power Generation, Inc.
|Turbine airfoil cooling system with elbowed, diffusion film cooling hole
|Jul 21, 2009
|Florida Turbine Technologies, Inc.
|Turbine blade with film cooling slot
|Jun 21, 2007
|Aug 3, 2010
|Florida Turbine Technologies, Inc.
|Turbine vane endwall with cascading film cooling diffusion slots
|Sep 7, 2010
|Siemens Energy, Inc.
|Turbine airfoil with enhanced cooling
|Oct 26, 2010
|Honeywell International Inc.
|Percussion drilled shaped through hole and method of forming
|Oct 13, 2006
|Feb 15, 2011
|Florida Turbine Technologies, Inc.
|Turbine airfoil with continuous curved diffusion film holes
|May 31, 2011
|Cooling channel formed in a wall
|Aug 16, 2011
|Iowa State University Research Foundation, Inc.
|Momentum preserving film-cooling shaped holes
|Nov 15, 2011
|Florida Turbine Technologies, Inc.
|Shaped film cooling hole for turbine airfoil
|Nov 7, 2008
|Nov 15, 2011
|Florida Turbine Technologies, Inc.
|Multiple expansion film cooling hole for turbine airfoil
|Nov 29, 2011
|Florida Turbine Technologies, Inc.
|Film cooling hole for a turbine airfoil
|Aug 5, 2005
|May 22, 2012
|Tredegar Film Products Corporation
|Formed film, methods and apparatus for manufacturing same, and articles comprising same
|Jul 9, 2012
|Sep 3, 2013
|United Technologies Corporation
|Multi-lobed cooling hole array
|Jul 9, 2012
|Nov 5, 2013
|United Technologies Corporation
|Gas turbine engine component with impingement and diffusive cooling
|Jul 9, 2012
|Nov 19, 2013
|United Technologies Corporation
|Tri-lobed cooling hole and method of manufacture
|Mar 27, 2008
|Jan 14, 2014
|Siemens Aktiengesellschaft
|Eccentric chamfer at inlet of branches in a flow channel
|Aug 31, 2010
|Mar 18, 2014
|General Electric Company
|Components with conformal curved film holes and methods of manufacture
|Jul 9, 2012
|Apr 1, 2014
|United Technologies Corporation
|Multi-lobed cooling hole and method of manufacture
|Jul 9, 2012
|Apr 1, 2014
|United Technologies Corporation
|Gas turbine engine component with impingement and lobed cooling hole
|Jul 9, 2012
|Apr 8, 2014
|United Technologies Corporation
|Cooling hole with thermo-mechanical fatigue resistance
|Jul 9, 2012
|Apr 29, 2014
|United Technologies Corporation
|Cooling hole with crenellation features
|Jul 9, 2012
|May 27, 2014
|United Technologies Corporation
|Cooling hole with asymmetric diffuser
|Feb 1, 2010
|Jun 3, 2014
|United Technologies Corporation
|Method of creating an airfoil trench and a plurality of cooling holes within the trench
|Jul 9, 2012
|Jul 1, 2014
|United Technologies Corporation
|Multi-lobed cooling hole and method of manufacture
|Jul 9, 2012
|Oct 7, 2014
|United Technologies Corporation
|Cooling hole with curved metering section
|May 26, 2010
|Nov 4, 2014
|Cooling channel formed in a wall
|May 28, 2010
|Dec 9, 2014
|General Electric Company
|Articles which include chevron film cooling holes, and related processes
|Sep 27, 2011
|Dec 23, 2014
|General Electric Company
|Offset counterbore for airfoil cooling hole
|Mar 11, 2014
|Mar 17, 2015
|United Technologies Corporation
|Cooling hole with crenellation features
|Jul 9, 2012
|May 5, 2015
|United Technologies Corporation
|EDM method for multi-lobed cooling hole
|Aug 18, 2014
|Aug 25, 2015
|Electrode for forming a cooling channel in a wall
|Sep 28, 2012
|Feb 23, 2016
|Honeywell International Inc.
|Cooled turbine airfoil structures
|Jul 9, 2012
|Mar 1, 2016
|United Technologies Corporation
|Gas turbine engine component with multi-lobed cooling hole
|Jul 9, 2012
|Mar 8, 2016
|United Technologies Corporation
|Gas turbine engine component with converging/diverging cooling passage
|Jul 9, 2012
|Mar 15, 2016
|United Technologies Corporation
|Gas turbine engine component with cusped cooling hole
|Jul 7, 2011
|Jun 28, 2016
|Ihi Corporation
|Turbine blade and engine component
|Aug 23, 2001
|Feb 27, 2003
|Ducotey Howard S.
|Method for repairing an apertured gas turbine component
|Jan 16, 2003
|Jul 24, 2003
|Snecma Moteurs
|Moving blade for a high pressure turbine, the blade having a trailing edge of improved thermal behavior
|Jan 27, 2004
|Jul 28, 2005
|Ardeshir Riahi
|Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
|Sep 17, 2003
|Oct 20, 2005
|Heeg Robert J
|Teardrop film cooled blade
|Jun 23, 2004
|Dec 29, 2005
|Ching-Pang Lee
|Chevron film cooled wall
|Oct 4, 2004
|Apr 6, 2006
|Alstom Technology Ltd
|Gas turbine airfoil leading edge cooling construction
|Oct 6, 2004
|Apr 6, 2006
|General Electric Company
|Stepped outlet turbine airfoil
|Jul 25, 2006
|Feb 1, 2007
|Cooling channel formed in a wall
|Aug 5, 2005
|Feb 8, 2007
|Tribble James D
|Formed film, methods and apparatus for manufacturing same, and articles comprising same
|Dec 2, 2005
|Jun 7, 2007
|Siemens Power Generation, Inc.
|Turbine airfoil cooling system with elbowed, diffusion film cooling hole
|May 7, 2007
|Nov 13, 2008
|Siemens Power Generation, Inc.
|Turbine airfoil with enhanced cooling
|Aug 20, 2007
|Feb 26, 2009
|Honeywell International, Inc.
|Percussion drilled shaped through hole and method of forming
|Mar 27, 2008
|May 13, 2010
|John David Maltson
|Eccentric chamfer at inlet of branches in a flow channel
|Feb 1, 2010
|Aug 5, 2010
|Rolls-Royce Deutschland Ltd & Co Kg
|Method for the provision of a cooling-air opening in a wall of a gas-turbine combustion chamber as well as a combustion-chamber wall produced in accordance with this method
|Sep 16, 2010
|Cooling channel formed in a wall
|Sep 23, 2010
|General Electric Company
|Method of Using and Reconstructing a Film-Cooling Augmentation Device for a Turbine Airfoil
|Jun 9, 2011
|United Technologies Corporation
|Article having diffuser holes and method of making same
|Aug 4, 2011
|Jesse Gannelli
|Method of creating an airfoil trench and a plurality of cooling holes within the trench
|Sep 27, 2011
|Mar 28, 2013
|General Electric Company
|Offset counterbore for airfoil cooling hole
|Jul 7, 2011
|May 2, 2013
|Ihi Corporation
|Turbine blade and engine component
|Sep 28, 2012
|Apr 3, 2014
|Honeywell International Inc.
|Cooled turbine airfoil structures
|Oct 4, 2012
|Apr 10, 2014
|Honeywell International Inc.
|Gas turbine engine components with lateral and forward sweep film cooling holes
|Oct 31, 2012
|May 1, 2014
|General Electric Company
|Components with asymmetric cooling channels and methods of manufacture
|Dec 10, 2012
|Jun 12, 2014
|General Electric Company
|Turbo-machine component and method
|Dec 28, 2012
|Jul 31, 2014
|United Technologies Corporation
|Gas turbine engine component cooling arrangement
|May 28, 1997
|Jul 9, 2003
|Kabushiki Kaisha Toshiba
|Cooling of a structure for use as a turbine blade
|Aug 14, 2008
|Feb 25, 2009
|Honeywell International Inc.
|Composant comprising a percussion drilled shaped through hole providing Coanda effect and method of forming the same using laser percussion driling
|U.S. Classification
|International Classification
|Cooperative Classification
|European Classification
|Dec 23, 1985
Owner name: UNITED TECHNOLOGIES CORPORATION, HARTFORD, CONNECT
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:FIELD, ROBERT E.;REEL/FRAME:004501/0662
Effective date: 19851210
|May 30, 1989
|Certificate of correction
|Sep 17, 1991
|Fee payment
Year of fee payment: 4
|Sep 11, 1995
|Fee payment
Year of fee payment: 8
|Sep 23, 1999
|Fee payment
Year of fee payment: 12


text:
Shimano® Solstice / Abu Garcia® Vendetta 6'6" Spinning Combo
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Shimano® Solstice / Abu Garcia® Vendetta 6'6" Spinning Combo is a perfect balance of strength and sensitivity! SAVE BIG !
Not to mention, powerful, too... you can practically send your casts to the next county with this rugged Reel. The Abu Garcia® Vendetta Rod boasts multi-directional graphite fibers around the 30-ton graphite blank for the ultimate combination of strength and sensitivity. The Shimano® Solstice Reel has a propulsion line management system and 3 stainless steel ball bearings for long, smooth, powerful casts.Abu Garcia Rod:
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subset: commoncrawl


text:
Another successful #cometryhockey event in the books with over 50 kids! Thank you volunteers! @MinnHockey @usahockey https://t.co/l6zU1Mtl95
Northern Lakes Youth Hockey Association will be holding its second annual golf tournament on Sunday, August 28, 2016 at Deacon's Lodge in Breezy Point. The event will be a four person scramble with a shot-gun start at 1:00 pm with a dinner and awards banquet following. The proceeds will be used to help fund association needs such as paying for ice time, equipment, buses for transportation between the two arenas we use, etc. Northern Lakes Youth Hockey Association is a non-profit 501c(3) volunteer-driven organization serving 250 players across the school districts and communities of Aitkin, Crosby-Ironton, Crosslake, Pequot Lakes and Pine River-Backus.
Sponsorship opportunities are available - see below for the details!
Information is attached below. Please click on the link below to register. We look forward to seeing you at this great event!
Click on the link to register!
The best way to communicate with the players/parents is through email and the website. A majority of the time you will receive emails from your teams coach or team manager. When they send an email out, it is meant to let you know important information regarding your team. To make sure that everyone receives the information in a timely manner, we need to make sure that all emails associated with your player are in your player's profile. By going into your profile, you can add emails to make certain that Mom, Dad, and the player (if they have email) will receive information. Below is a link to the NGIN Help. Click on the link and you should be brought to a webpage that has instructions for adding emails to your account.
***NOTE*** Make sure that you look at the "Contact Preferences" and that the email box is checked for Northern Lakes Lightning Youth Hockey Association. You will not receive emails from the association if it is not checked.
Another useful tool for getting information/schedules for your players team is the NGIN Sports App for your smart phones. The App is available for both iPhones and Droids. Go to your respective App page and query NGIN Sports App. Upload it to your phone and follow instructions from there. The App will allow you to follow one team for free. If you have players on two different teams, there is an annual subscription of $1.99. The App will have the teams schedule and game results among other things. If you have a Peewee, Bantam, or 12U, you will see that there are two teams to select from; one will be from the District 15 Website and the other from ours. If you want schedule information, you will need to pick the team from our site.
Any questions, you can email me at firstname.lastname@example.com
Thank you,
Brent Nybakken
Board Minutes and Agenda's will be posted as soon as they become available. You will find them under the "Board" tab above. The Board will attempt to get the agenda out for the meeting as soon as it is set. Please be patient as the agenda changes frequently prior to the meeting. Minutes will be placed on the website as soon as the Board approves the minutes, typically at the following meeting.
We are hiring meat raffle employees for:
Saturday evenings 5:30 p.m. at the Bourbon Room in Crosslake
Contact: Sharon 218.821.0211
Pay $35 each night
Hat Trick - $1,000
Houston Ford, Pine River: http://houstonfordpineriver.com/
North Central Medical Supply, Brainerd: http://www.ncmedicalsupply.com/
One-Timer - $600
Deerwood Bank, Deerwood/Brainerd: http://deerwoodbank.com/
Face-Off - $300
Hallett Community Center, Crosby: http://hallettcenter.com/
Hockey House, Brainerd: http://hockeyhousemn.com/
Lands End Development, Crosslake: http://landsenddev.com/
Please use the NLYHA Schedule as the Master Calendar for NLYHA. Please check the calendar regularly for updates. The calendar is dated in the upper right corner.
Click on this link and you will be taken to the iCal Instructions page. Hopefully this will help you with importing the calendar for your team into your smart phone, Google Calendar, or Outlook Express.
No upcoming events found.
Another successful #cometryhockey event in the books with over 50 kids! Thank you volunteers! @MinnHockey @usahockey https://t.co/l6zU1Mtl95
@Hockeyhousebrd thank you for coming to our banquet last night and for giving away a free week @mnhockeycamps to a player! #youareawesome
@DaveSpehar thanks for speaking! Great message we appreciated your time and wisdom! https://t.co/3jsFRmve9g
#cometryhockey for #free ages 4-8 on Sunday April 3rd! For details visit: https://t.co/Is8Gv3UiPh
Lightning families please register to attend the banquet by March 31! On our homepage https://t.co/7aHlthfFAz
Look at them all! So much fun at #cometryhockey #girlsonly #girlsplayhockey #noboysallowed @usahockey @MinnHockey https://t.co/G92b7iRLuO
20 girls came to our #cometryhockeyevent #girlsplayhockey #realgirlsplayhockey #girlsonly @usahockey @MinnHockey https://t.co/hLsBqkiDiA
Let's go #GrandRapids you've got this! #battleofthenorth #statetouney16 #stateofhockey
Congrats #pwb on your awesome season! It ended today with a 7-4 loss to Crookston at #regions #golightning @YouthHockeyHub
Sending good vibes to our #pwb as they head into 3rd period trailing 5-4! #letsgoboys #skatetostate #golightning
#10u ends their season with a 7-2 win over Fergus Falls. #golightning #greatseason
Congrats #pwb on the #overtime win today at #regions! 5-4 over STMA! #roadtostate #golightning


text:
We loved this property! Small in size so easy to catch an elevator and get a restaurant table. We were on tall main building, the small area to the side doesn't seem as nice. Balcony allowed us to stand outside, but not sit. We had a fabulous ocean-front room. Pool and ocean both very short walks. Pool bar food fantastic and reasonably priced. Wonderful location for walking to many restaurants and bars. Would definitely stay again! Huge bathroom closet too!
- Official Description (provided by the hotel):
- Enjoy stunning surroundings and 44 breathtaking acres along the Intracoastal Waterway at the Bahia Mar Fort Lauderdale Beach hotel- a DoubleTree by Hilton Hotel. Located near the International Swimming Hall of Fame, the Bahia Mar Fort Lauderdale Beach hotel is a water taxi ride away from the shops, restaurants and nightlife of Las Olas Boulevard. Stay active with water sports, indulge the option to sail away on a cruise or simply relax on the white sandy beach. Bahia Mar is only a short drive from the Fort Lauderdale International Airport and Port Everglades Cruise Terminal. ... more less
- Reservation Options:
- TripAdvisor is proud to partner with Booking.com, Expedia, Hotwire, BookIt.com, Hilton Hotels, Travelocity, Hotels.com and Odigeo so you can book your Bahia Mar Fort Lauderdale Beach - a Doubletree by Hilton Hotel reservations with confidence. We help millions of travelers each month to find the perfect hotel for both vacation and business trips, always with the best discounts and special offers.
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text:
I'm facing the problem with PHP response. I used Ajax with 3 seconds delay to check the user's logs. When the user account used simultaneously with two users, one must be kicked. I used to track the log id in db if equal with the session. The problem is some users are getting kicked even there is no other user using his/her account. I tried to
print_r the query statements and it is returning different values. It might be the response for other users.
I'm using IIS server and FastCGI for PHP response.
Can somebody tell me how this possible and give me ideas to solve this issue? Thanks.
Here is some of the codes :
Checking logs in DB using Ajax:
public function CheckLogStatus( $name, $email, $sess_code ) {
$qry = "Select log from $this->tablename where name='$name' and email='$email'";
//when I print this statement it returns different values of $name and $email
$result = mysql_query( $qry ) or die(mysql_error());
if( !$selResult = mysql_fetch_array($result) ) {
return false;
if(!isset($_SESSION)) {
if( !isset( $selResult['log'] ) && $selResult['log'] != '' ) {
if( $selResult['log'] != $sess_code ) {
return false;
return true;


text:
Legislature in session; medical marijuana program launched
Last update: March 23, 2016
Minnesota is in the second half of a two-year legislative session. The first half of the 2015-2016 session brought about some slight changes to the restrictive medical marijuana program enacted in May 2014. While most of the changes were technical, one provision sped up the timeframe regarding when the health department could add intractable pain as a qualifying condition. As a result, by July 2016, patients suffering from this condition will be eligible to register for the program. Lawmakers have filed several bills seeking further reforms to the program. Be sure to sign up for our Minnesota-specific action alerts to stay up to date on marijuana policy reform in the Land of 10,000 Lakes.
Meanwhile, the state has been among the quickest to fully implement a comprehensive medical marijuana program. Currently, three dispensaries are open in the state with five more scheduled to open later this spring. Minnesotans with qualifying conditions who are interested in enrolling in the program, and healthcare practitioners who are interested in certifying some of their qualified patients, should contact the Minnesota Department of Health for details. Unfortunately, there have been reports that the program has resulted in costly medicine and difficult access. Hopefully these issues will be addressed as the program continues to take root; if not, we will seek legislative changes.
Statewide television ad campaign highlights the need for medical cannabis in Minnesota
On April 2, 2014, MPP and Minnesotans for Compassionate Care began running television commercials across the state highlighting just one of many Minnesotans, and his mother, who could benefit from passage of a compassionate law. You can watch the ad here.
On April 8, 2014, we began airing a second ad featuring Patrick McClellan (above), who has found that medical cannabis alleviates his debilitating spasms far more safely and consistently than prescription medications. The ads helped force the governor to allow a medical marijuana bill through — though it was more limited than we would have liked. It has resulted in a limited but successful medical marijuana program, which has already been expanded to include intractable pain. Yet, many patients still have to travel great distances to access medical cannabis, whole plant cannabis is not allowed, and other patients are left behind completely due to their conditions being excluded
Please email your lawmakers regarding their support — or lack thereof — of Minnesota's medical cannabis law and encourage them to continue to help protecting all the suffering who can benefit from medical cannabis.
Learn about Minnesota's marijuana laws
In 2012, there were 12,051 marijuana-related arrests in Minnesota. Sixty-two percent of these arrests were for marijuana possession. While the penalty for a first offense of possessing a small amount of marijuana in Minnesota is a $200 fine and mandatory drug education, having two ounces could land Minnesotans in jail for five years! These arrests hit minority communities the hardest. According to data from the ACLU, African Americans in Minnesota are nearly eight times as likely to be arrested for marijuana possession as their white neighbors!
Ask your lawmakers to remove penalties for adults who choose to use, possess, or purchase marijuana and to create a system that regulates and taxes the production and distribution of marijuana similarly to alcohol. You can learn more about Minnesota's marijuana penalties and enforcement by reading this report by Jon Gettman, Ph.D.


text:
Lori Fulton is an Assistant Professor of teacher education at the University of Hawai'i at Manoa. A former elementary teacher, she has been involved in the process of teacher change and professional development in the area of science for over 15 years. Lori received the NARST Outstanding Doctoral Research Award in 2013 for her work on writing in science.
Brian Campbell is a curriculum developer at the University of California, Berkeley where he focuses on creating instructional materials and professional development opportunities for science in elementary schools. He works with teachers and districts to refine the use of science notebooks in classrooms focusing on formative assessment and the connections to language arts. He enjoys learning especially from his two daughters.


text:
Seriously... I do not think I could ever do this. Judging from the way she speaks, I am guessing she is Korean-American.
Monday, April 30, 2012
Eating Live Octopus
Seriously... I do not think I could ever do this. Judging from the way she speaks, I am guessing she is Korean-American.
4 comments:
- Sana Khatri said...
The fun is in the details! I love pouring over paint chips and fabric samples, literature review help and flooring alike!
- December 24, 2012 at 6:27 PM
- essayswriters said...
I tell you why. Because humans are not animals, and our cavemen days are long past when raw meats would be eaten. I believe even thousands of years ago they still killed their prey before attempting to eat it. Also, octopus are cannibal and eat each other in nature, so would that mean human cannibalism is also acceptable for you? Hell, if animals do... To see more info please visit http://essayswriters.org/assignment/.
- September 29, 2013 at 8:33 PM
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Research shows that skilled readers perform better in all academic areas. Reading comprehension involves reading with fluency, building vocabulary, and continually developing reading skills.
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Police say woman held, beaten for a week by husband
SOUTH SALT LAKE — A man who police say held his wife hostage for a week and repeatedly beat her, sometimes in front of their children, has been arrested and charged.
On Dec. 26, Deysy Beltran told police she got into a fight with Carlos Ortiz, 32, in their bedroom, and Ortiz began punching and kicking her. He then brought their 11- and 9-year-old children into the room and "made them watch as he beat their mother," according to the charges. One of the children later told police that Ortiz would "come and get us so we can watch him hit her. Sometimes he laughs," the charges state.
Beltran was beaten until she was knocked unconscious, police said. Ortiz, however, shook her and told her not to fall asleep. She told him she needed to go to the hospital, but Ortiz declined, the charges state.
From Dec. 26, 2012, until Jan. 2, 2013, Ortiz did not allow Beltran to leave the house and "followed her everywhere," according to court documents.
The only exception was on Dec. 30 when Ortiz became ill and demanded that Beltran drive him to the hospital. He beat her along the way while their children watched from the back seat, according to charges. Beltran eventually pulled to the side of the road, got out and walked away. Ortiz initially drove off but then came back and allegedly dragged Beltran back into the car.
On Jan. 2, Ortiz fell asleep and Beltran ran to her brother's house for help.
Ortiz was charged in 3rd District Court Thursday with aggravated kidnapping, a first-degree felony; aggravated assault, a second-degree felony; two counts of domestic violence in the presence of a child, a third-degree felony; and damage to a phone, a class A misdemeanor.
Twitter: DNewsCrimeTeam
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Skip to comments.Texas' cities among fastest-growing in US
Posted on 05/24/2013 12:35:03 PM PDT by Responsibility2nd
Email 0Share 0Tweet0Share0Print......
Eight of 15 cities with the fastest growth in the United States are in Texas, according to the latest data released by the U.S. Census Bureau.
Estimates released Thursday also show that half of those cities in the nation with the largest total population increases are in Texas. And Houston added more than 34,500 people to reach 2.2 million inhabitants only second to New York City in total population gains in the year that ended last July.
The Central Texas town of San Marcos is the fastest-growing city in the U.S., increasing by 4.9 percent. It also surpassed the 50,000-population mark, the minimum threshold that cities had to reach to be included in the bureau's list.
Other cities with rapid population growth: Midland and Odessa in West Texas; Conroe, just north of Houston; and the Austin suburbs of Cedar Park and Georgetown, as well as Frisco and McKinney, located north of Dallas.
No other state had more than one city in the top 15 list.
Of the 10 U.S. cities with the largest total gains, half are in Texas: Houston, San Antonio, Austin, Dallas and Fort Worth.
(Excerpt) Read more at news.yahoo.com ...
God help Texas.
God help us. I don't consider this a good thing at all.
True! We got enough Californian here now, especially Austin, and don't need any more.
Amen bro
Not sure how good this is...The liberal human viruses coming soon to a Texas city near you...
They weren't born in Texas, but they got there as soon as they could (so they could mess it up).
I was surprised to learn that little ol quaint Austin, is close to becoming a member of the 10 largest cities in America, I realized that the traffic was worse, but that detail sneaked up on me.
Personally, I think America was just fine in 1970 with about 200 million people, I know that Austin and San Diego, and Los Angeles, and Houston were better cities.
Oh, boy (as Texan Buddy Holy sang.) I guess we oughta be thankful AP didn't write "Texas's cities", still, "Texas cities" would of done just fine.
....and this growth would be Hispanic?????
I don't see Texas ever becoming California. Not the feel good, can't we all get along, planet first, who's your therapist culture. Perhaps in Colorado, but not Texas.
Minority demographics are a much bigger threat to the culture of Boone, Bowie and Travis.
Scary news. Are we becoming Texico or Texifornia? Does it make any difference?
All the gays and other liberals are descending on Texas to push their agenda. And then they will move somewhere else. Locusts.
Not everyone in the US is enchanted with Obama's Marxist nanny state; there remain a few - statistically speaking - who are aware of America's great legacy and value freedom.
Don't mess with Texas!
Texas citie's?
It's a liberal wetdream to hijack Texas' electoral votes and Senate seats.
This can be a two edged sword. It makes me sick at my stomcah to hear, "Well back in Jersey we did it this way"
In 2004, Kerry signs filled their yard and they continually destroyed their next door neighbor's McCain yard sign (until her oldest son stated he would kick their a$$ if it happened again). In 2008, they were the only demented a$$ clowns in the area to have Obamunist for Tyrant signs on their front lawn. Not quite sure what happened, but during the 2012 election year, no signs. After seeing what these parasites have done to states like Colorado and New Mexico, I can only hope that they are all moving to Austin or Houston.
Resistane is futile. You will be assimilated!
The growth is from people liberal business killing states.
Many of them do not make the connection between great cost of living and business climate and the leave me the heck alone government.
That's affirmative.
Florida is moving left due to migrants from other States
Was not a problem when it was just retirees. Even the economically liberal were still social conservatives
It got bad when the NY Hispanics came down. Liberal voters and dependent on govt...there was an article posted recently that 37% of Puerto Rico was on food stamps. Believe it.
Then you have the Haitians and Dominicans...and other Latin Americans. More government, more Democrats
Then the state GOP moves left....ouch
Texas can stop this. First....no more RINO governors. Florida's big mistake
It's going to be one BAM in the Houston area if we have another hurricane like Ike. Been awfully quiet in the Gulf since he came and went. Evacuation five years ago was a mess. Lot of people who have lived here for a long time are ill equipped to deal with hurricanes, don't even want to think about the newbies.
Not necessarily. Perhaps in the southern cities. But a lot of the growth is people/companies fleeing other states to come here.
I grew up in Sherman and now live in McKinney. The northern burbs of Dallas have exploded with growth. Frisco used to be maybe 10,000 people at the most ... some neighborhoods had dirt roads. They're now at 121k.
McKinney was about 35,000 way back when. Now we're that plus 100k. Expected total growth will be pushing half a million once all areas of the city limits are populated.
There's no way those explosive numbers are from hispanic immigration.
I read recently that the City Council was considering a Sexual Orientation Regulation...meaning trannies could use the same bathroom as your little kids. Not sure if this has passed, yet.
The SA Mayor was raised by a La Raza founder, IIRC. His leftist views are NOT good for the city. Wake up, San Antonio!!
Agree and thanks for the warning from FL!
No RINO Govs OR legislature!!
The TX legislature is trying to stop Tea Party groups from being a force to keep out RINO's, by limiting donations these groups can make to conservative candidates. Hopefully Gov Perry will veto this ridiculous bill (SB 346).
BTW- I agree with everything you said. The Castro's are bad news.
Well, there goes the aquifier. This time last year, the Edwards Aquifier was around 660 acre feet of water. Today, it's down to 640 acre feet. The drought may still be hitting hard, but the influx of more people in the San Antonio/Austin area really stresses it.
Californians and Mexicans = blue state within 5 years
"there remain a few - statistically speaking - who are aware of Americas great legacy and value freedom."
You betcha.
Republicans and conservatives now completely control 25 states via the legislature and governorships. Liberal, purse-carrying wimps control 11 states. Those 25 states represent more than half the population of the US.
Americans are voting right on a state level. Liberals are controlling voting booths via the Nazi Soros to illegally pour leftists into Washington.
We are heading for a classical confrontation of states vs the criminal fascist syndicate occupying Washington.
Good luck to us, the good guys,
Disclaimer: Opinions posted on Free Republic are those of the individual posters and do not necessarily represent the opinion of Free Republic or its management. All materials posted herein are protected by copyright law and the exemption for fair use of copyrighted works.


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- Class of 1974 Kenneth Farrington
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An ongoing effort to install steel mesh on balconies in the Jeffco jail is expected to reduce the risk of inmates attempting suicide and should be finished next year, according to a Sheriff's Office official.
The project targets high-risk areas, including maximum-security modules on the jail's sixth and seventh floors, and pre-sentencing areas on the fourth floor, said Dan Gard, chief of the sheriff's support services division, who appeared before the county commissioners March 22 to ask for additional funds for this year's portion of the project.
By Gabrielle Porter
Staff Writer
The medical provider being sued by the family of a Jeffco jail prisoner who died in her cell after waiting hours in vain for medical attention has asked a federal judge to dismiss parts of the lawsuit, calling the complaint "scattershot."
Attorneys for the county say a revamped agreement with Comcast that has taken years to negotiate should be ready to finalize by mid-April.
David Wunderlich, assistant county attorney, told the county commissioners March 29 that pressure applied over the last several weeks has helped push along the process of changing the way the company pays to access its cable lines on county property.
The driver suspected of hitting a sheriff's deputy Wednesday evening at the scene of a massive pileup on eastbound I-70 at the Lookout Mountain exit turned himself in to the State Patrol about 2 a.m. Thursday.
Jeffco's battle continues with Comcast over finalizing a change in how the company pays to use its cable lines on county-owned property, with commissioners threatening to temporarily raise access fees until a new deal is signed.
West Metro Fire Chief Don Lombardi received accolades from fire district board members who evaluated his performance this past year.
"Chief Lombardi's leadership is excellent. He is always looking at ways to save money," the evaluation stated. "The chief is an outstanding leader and is respected by his employees, firefighters and the board of directors."
A civic-minded citizen pursued two shoplifting suspects through the parking lot of the Burlington Coat Factory on West Bowles Avenue on March 24, jumping into their vehicle in an attempt to thwart the perpetrators.
The black minivan began speeding away with its side door open and the good samaritan inside, until the two female suspects noticed they had company and screeched to a stop, yelling at their unwanted passenger to get out. They then fled.
Despite concerns about potential conflicts of interest, Jeffco's county commissioners have decided to re-appoint a current Planning Commission member after another member stepped down suddenly.
The commissioners decided March 15 that Vince Harris will serve out the last two years of the term of Courtney Ahuja, who resigned March 9 because of the demands of a new job. Jeffco's seven-person Planning Commission makes land-use and planning recommendations to the county commissioners.
From the Syrian refugee crisis to the San Bernardino terrorist's cell phone to Colorado's caucus-versus-primary debate, Congressman Jared Polis' question-and-answer session with the Mountain Area Democrats on Saturday covered myriad current events and issues.
Polis, who is up for re-election this year, told area Dems that November's results will be pivotal for the party at all levels, and that control of the U.S. Senate is up for grabs.
Commissioner slams RTD over Golden light-rail crossing
County Commissioner Don Rosier on March 22 expressed outrage about the light-rail crossing at West Sixth Avenue and Johnson Road near the county courts building, which he described as dangerous.
Rosier said he has sent e-mails to the Regional Transportation District about the crossing, where he says the train often crosses Johnson Road even when oncoming traffic has a green light.
Copyright © 2016
Columbine Courier is your source for local news, sports, events, and information in South Jefferson County, Colo., and the surrounding area.


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Oh… I see how it is. Using me for my awesomeness are you now?
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Mom, why do you do this to me, to yourself.
Because of what has happened over the few years, I hate myself.
I hate living.
Mommy, I don't wanna live no more.
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