JPS611805A - Blade used in gas turbine engine - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention]

This invention relates generally to gas turbine engines and, more particularly, to coolable hollow turbine blades of such engines. The efficiency of a gas turbine engine is directly proportional to the temperature of the turbine gas that is routed from the engine's combustor through the high-pressure turbine nozzle and allowed to flow over the turbine blades.
Ru. For example, in a gas turbine engine with relatively large turbine blades, such as blades having a root-to-tip dimension greater than about 1.5111 mm, the temperature of the turbine gas is 2.5 mm.
Close to 700°F is typical. To withstand these relatively high gas temperatures, these large vanes are constructed of known high-grade materials and typically incorporate conventional, known types of cooling techniques. Turbine blades are typically cooled using a coolant such as m-high air from a compressor. This discharged air is utilized by various structural elements to provide film, impingement and/or convective cooling of the turbine blades. Typically, the vanes have serpentine coolant passages and various features for the cold section, such as turbulence-enhancing ribs, i.e., turbulators that enter the serpentine passages approximately 0.0010 inches from the sidewalls of the vanes. . General f
Inside, you can use a cylindrical bottle, which/,+
<Snake (in one passage, between the opposite side walls of the wings; until the middle of the male)

[Can be fully extended1] Typically, the leading edge of the blade is the heaviest part and requires relatively complex special cooling features. For example, the leading edge has a leading edge cold frontage (1)
Jl! This type of cooling opening has the effect of improving the boundary cooling B1. Or a meandering passageway at the leading edge]
An insert can be provided to enhance the cooling effect. Alternatively, the serpentine path at the leading edge can be stepped with turbulators and pins to improve heat transfer. Gas turbine engines with relatively small turbine blades, e.g. less than about 1.5 inches from root to tip,
Because of its relatively small dimensions, it is not possible to utilize most of the cooling features of the JZ (as described above) for the puppet blades, and therefore, the turbine gas temperature is approximately 2 , 300"F. Therefore, a small gas turbine engine (Y,v)2°300°F7'IJ〒approx.
, 700'F range, resulting in an inability to achieve the higher operating efficiencies associated with higher turbine gas temperatures in the range of ,700'F. Accordingly, one object of this invention is to provide a new and improved tarhi/vane with cold 741 characteristics. Another object of this invention is to provide a compact turbine blade with new and improved cooling features that are operative to withstand turbine gas temperatures greater than about 2.300'F. Another object of the invention is to provide a compact turbine blade with cold section features that have improved heat transfer coefficients. Another object of this invention is to provide a new and improved compact turbine blade using cooling features that are relatively simple and easy to manufacture. SUMMARY OF THE INVENTION A gas turbine blade in accordance with a preferred embodiment of the present invention has an internal coolant passage having a width and a longitudinally extending inner coolant passage having a height E disposed substantially perpendicular to the axis of the coolant passage. It has a plurality of spaced apart substantially straight turbulence lips.The ratio E/D is about 0.
．． preferably within the range of 0.07 to about 0.33;
The height E of the ribs is within the range of about 0.0101]1 to about 0.025 inches. While the novel features considered unique to the invention are set forth in the claims, the invention itself as well as other objects and advantages will become apparent from the following detailed description in conjunction with the drawings. Detailed description of the gas turbine in Figures 1 and 2! used for leapfrog1
An example turbine blade 1o is shown. The vane 10 has a leading edge 12), a trailing edge 14, and first and second sidewalls 16,18 extending therebetween. The first side wall 16 is generally convex in profile and constitutes the suction side of the vane 10. The second side wall 18 has a generally concave profile and constitutes the pressure side of the vane 1o. Furthermore, a stand 20 on which the blade 10 is placed at the root 22 of the blade 1o.
including. The vane 1o also has a tip 24. Relatively hot turbine gases received from the combustor of the gas turbine engine are passed through high pressure turbine nozzles (not all shown) and flow over the blades 10 from the tip 24 to the root 22. The platform 2o is provided to define the radially inner boundary of the turbine gas flow. The blade 1o is attached to the rotor disk (
It also has a tenon 26 for attachment (not shown). In one embodiment of the invention, the vane 1o further has a preferably serpentine coolant passage 28, which is arranged between the first and second side walls 16.18, for cooling the vane 10. It acts to pass the coolant through it. The coolant passage 28 has one inlet 3o provided in the tenon 26;
Through this inlet enters a coolant 32, such as air, received from a gas turbine engine compressor (not shown). Vane 10 further includes a first partition 34 extending radially outwardly from root 12 toward tip 24 . A first septum 34 extends between the first and second sidewalls 16.18 and is spaced from the leading edge 12 and tip 24. The first partition wall 34 and the first partition wall 34 and the front edge 12
The first and second side walls 16.18 therebetween define a first portion □ of the serpentine coolant passage 28; ie, a leading edge passage 36. Additionally, the vane 10 has a second partition 38 extending radially inwardly from the tip 24 toward the root 22. A second spacing N38 extends between the first and second sidewalls 16.18 and is spaced from the trailing edge 14, the first septum 34, and the root 22. A second portion of the coolant passage 28, a mid-chord passage 40, is defined between the first bulkhead 34, the second bulkhead 38, and the first and second side walls 16.1B. Second bulkhead 38
, the trailing edge 14 and the first and second sidewalls 16.18 define a third portion of the coolant passageway 28, a trailing edge passageway 42. The first passage 36 and the second passage 40 are in flow communication with each other via a first vent passage 44 . The first bend channel 44 is formed between the tip 24 and the first partition wall 3'4.
between the radially outer ends 34a of and the second bulkhead 38
, the front 1i12 and the side walls 16.18. The second passage 4o and the third passage 42 are the second vent passage 4
The flow communicates with each other via 6. Second bend channel 4
6 is the radially inner end 38 of the root 22 and the second partition 38;
a and between the trailing edge 14 and the first spacing W34 at the root 22 and the first and second side walls 16.18. Further, the vane 10 is provided at the trailing edge 14 and has a plurality of trailing edge openings 48 in flow communication with the trailing edge passageway 42. A plurality of tip cooling openings 5o are provided in the tip 24 and are in flow communication with the first bend channel 44 and the third passage 44. In operation, coolant 32 enters serpentine coolant passage 28 through inlet 30, first passage 36, first bend passage 44, second passage 40 . a second bend flow path 46;
It sequentially flows through third passageway 42 and exits through trailing edge opening 48 . More specifically, 1 of the refrigerant entering the inlet 30
00% flows through leading edge passage 36. After this, approximately 1.0% of the coolant 32 continues to pass through the passage 4o of jF12 to the third
It flows into the passageway 42 and exits from the trailing edge frontage 4th. A relatively small portion, e.g. 15 to 20%, of the coolant 32 is transferred from the first vent passageway 44 and the third passageway 42 to the tip opening 5.
0 and improves the cooling effect of the tip @24. For example, the blade 10 has a turbine gas temperature of about 2°300'.
It is effective for use in small gas turbines with temperatures higher than 2,700°F. From the base 22 to the tip 24
The length of the vane 10 is less than about 1.5 inches, and in this embodiment is about 1.0 inches. The vanes 10 are made of conventional hot crack or superalloys. In order to effectively cool the blades 10 in such a high temperature environment, the present invention provides a plurality of turbulence ribs 52 within the coolant passages 28. As shown in FIGS. 1, 2, and 3, turbulence ribs 52 are preferably generally straight and vertically spaced. These ribs are on both side walls 1
6.18 and is disposed generally perpendicular to the direction of flow of coolant 32 as indicated by longitudinal axis 54 of coolant passageway 28 . As shown in particular in FIG. 3, each rib 52 has a height E, relative to the width between the side walls 16, 18 of the coolant passage 28.
The ratio E/D has a value greater than about 0.07. Preferably, the ribs 52 on the side wall 16 are staggered with respect to the ribs 52 on the side wall 18 and are equally spaced therebetween. Although turbulence ribs are known in the art, they typically
/D is less than about 0.07. This is due to several reasons. For example, turbulence ribs have been found to be effective in increasing the heat transfer coefficient due to commonly known convection. However, the height E of the turbulence ribs is directly proportional to the pressure drop that occurs in the flow path provided with such ribs.Furthermore, the turbulence ribs create turbulence that improves heat transfer; If made too large, flow separation occurs downstream of the ribs, which greatly reduces or eliminates convective heat transfer, thus avoiding substantial pressure drops through turbulent ribs and reducing the risk of flow separation. To reduce turbulence, conventional turbulent flow 1 typically has a ratio E/D of less than about 01O7 and a height E of about 0.
．． 010 inch glue 1 is used. In this invention, from the test results, the height [is about 0°010 inches to about 0.025 inches, and the ratio E/D is about 0°07 to about 0.
．． It has been found that the use of turbulent ribs 52 of 333 substantially increases the convective heat transfer coefficient. Preferred rib 5
2 occludes a significant portion of the coolant 32 (e.g.
As shown in the drawings, up to approximately 67% of the flow area within the coolant passages 28 may become obstructed (resulting in an increased pressure drop in the coolant passages 28). The improved heat transfer ability of the oxide film more than compensates for this undesirable characteristic. More specifically, FIG. 2 shows a graph illustrating the increase in convective heat transfer that can be achieved with the turbulence ribs 52 of the present invention. The horizontal axis of the graph is the ratio E/D, and the vertical axis is the heat transfer coefficient h due to convection of the turbulent rib 52 (rib) and the heat transfer coefficient h due to convection of the smooth wall (smooth wall).
Indicates the value divided by Curve 56 representing the ratio of convective heat transfer is based on tests performed on a configuration similar to that shown in FIG. Curve 56 is 0.15 and 0.333
Adjacent ribs 52 containing data points for the ratio E/D are separated by a distance S Lt, and the curve 56 contains data points for the ratio S/E k: 5.0 and IQ, Q (7). I'm here. Curve 56 shows that for a ratio E/D of 0°333, the ratio of convective heat transfer is approximately 7°5.
There is C. Therefore, it will be understood that the turbine blade 10 constructed according to the present invention is a blade that is relatively easy to manufacture in a cylinder. The vane 10 does not require relatively complex configurations known in the art, including, for example, leading edge film cooling holes. The blades 10 have significant convective heat transfer capabilities that allow the blades 10 to operate at temperatures greater than approximately 2,300 degrees Fahrenheit even though the blades are only about 1.0 inches long from root to tip. It can be operated by applying gas temperature. Referring back to FIGS. 1 and 2, ribs 52 extend within the coolant passageway 28 between the leading edge 12, the first bulkhead 34, the second bulkhead 38, and the trailing edge 14 of the sidewall 16.18. Of course, the ribs 52 can be adjusted to suit individual design requirements, with the height E varying from about 0.010 inches to about 0.025 inches, and the ratio E/D. is about 0.0
Note that it varies from 7 to about 0.333. A nominal height E of 0.020 inches is preferred. This is twice as large as a normal turbulent lip, but it improves heat transfer without causing undesirable flow separation. Since the leading edge 12 of the blade 10 is a critical area where some of the highest temperatures of the blade 10 are known to occur, another preferred arrangement of ribs 52 that improves heat transfer capabilities within the leading edge passageway 30 is , shown in FIGS. 5 and 6. In the example leading edge passageway 36 shown in FIG. . Leading edge 2nd lip 5
2b extends along the first side wall 16 from the first bulkhead 34 until it meets the end of the first rib 52a. First rib 52a
and the second ribs 52b are fast to each other or equally spaced from each other. An alternative embodiment of the leading edge passageway 36 is shown in FIG. As before, the first rib 52a extends generally to the leading edge 12, and the second rib 52b also extends generally to the leading edge 12. A third leading edge rib 52c is also provided, and at the leading edge 12,
It extends between the first and second ribs 52a, 52b along both the first and second sidewalls 16.18. Preferably, the first and second ribs 52a, 52b are aligned with each other at a common radius, and the third rib 52c is staggered with respect to the first and second ribs 52a, 52b, and are equally spaced. Having described what is considered a preferred embodiment of the invention, other modifications will occur to those skilled in the art from the foregoing description. For example, the first, second and third passages 36.40
．． Although vane 10 is illustrated having serpentine coolant passages 28 including 42, vanes 10 having only two passages may also be used. The second passageway 40 is in direct flow communication with the trailing edge opening 48 without the use of the second bulkhead 38. Additionally, although the use of staggered ribs 52 as shown in FIG.
．． 18 ribs 52 can also be used! both side walls 16
．． Although we have described the case where the ribs 52 are placed on the side wall 18, the heat transfer ability can be improved even if the turbulence ribs 52 are used only on one □ side wall. Of course, the present invention is not limited to use with small turbine blades, but can also be used with large agricultural blades. Smaller blades were considered to have improved cooling capacity due to their relatively simple and easy to manufacture features. □ Although this invention has been explained above, please understand that the scope of this invention is limited by the scope of the claims.

[Brief explanation of the drawing]

FIG. 1 is a side sectional view of a gas turbine blade according to an embodiment of the invention, FIG. 2 is a cross-sectional view of the turbine blade shown in FIG. 1 taken along line 2-2, and FIG. Connect the turbine blade to line 3-
Fig. 4 is a graph showing the ratio of the heat transfer coefficient due to convection of the turbulent rib shown in Fig. 1 to the heat transfer coefficient of a smooth wall against the ratio E/D, 5 is a cross-sectional view of the leading edge region of the turbine blade of FIG. 1 taken along line 5-5, and FIG. 6 is a cross-sectional view of another leading edge region of the turbine blade of FIG. 1 taken along line 5-5. It is a diagram. Explanation of main symbols 12: yi edge 14: trailing edge 16.18: side wall 28: meandering passage 52: turbulence rib

Claims (1)

[Claims] 1) A blade for use in a gas turbine engine, comprising a leading edge, a trailing edge, and first and second side walls extending between the leading edge and the trailing edge, the side wall being A coolant passage has a width D for passing the coolant in a direction substantially parallel to the longitudinal axis thereof, and one side wall is disposed within the coolant passage substantially perpendicular to the longitudinal axis. a plurality of longitudinally spaced substantially straight turbulence ribs, each rib having a height E, and having a ratio E/D greater than about 0.07. 2) The blade according to claim 1), wherein the ratio E/D is within a range of about 0.07 to about 0.333. 3) The vane of claim 1), wherein said height E is greater than about 0.010 inches and said vane length is less than about 1.5 inches. 4) The blade according to claim 1), wherein E is about 0.020 inches. 5) In the blade according to claim 1), the ribs are spaced apart from each other by a distance S in the longitudinal direction, and have a ratio S/E.
is within the range of about 5.0 to about 10.0. 6) The vane according to claim 1), wherein the rib extends along substantially the entire length of the side wall within the coolant passage. 7) The blade according to claim 1), wherein each of the first and second side walls has a plurality of turbulence ribs. 8) The blade according to claim 7), wherein the ribs on the first side wall are alternated with the ribs on the second side wall. 9) In the blade according to claim 2), each of the first and second side walls has a plurality of turbulent flow ribs, and the ribs on the first side wall are connected to the ribs on the second side wall. Feathers that are staggered against the ribs. 10) The blade of claim 1), having a root and a tip, the blade length from the root to the tip being less than about 1.0 inches. 11) In the vane of claim 1), the coolant passages and the ribs have the effect of enabling the vane to withstand turbine gas temperatures greater than about 2,300°F. Feather. 12) The blade according to claim 2) has a root and a first partition wall extending from the root, and the coolant passage is constituted by a meandering passage constituted by the first partition wall and the side wall. and extending along the leading edge.
and a second passageway disposed substantially parallel to and in flow communication with the first passageway, the rib extending from the first bulkhead to both the first and second sidewalls. A feather that extends along the leading edge. 13) The vane according to claim 12), wherein the rib in the first passage extends from the first bulkhead along the first sidewall generally to the leading edge. a rib, and the first partition wall along the second side wall from the first partition wall.
A vane comprising a leading edge second rib extending to the rib, said first rib and said second rib being alternating. 14) The vane according to claim 12), wherein the rib in the first passage extends generally from the first partition wall to the leading edge along the first sidewall. a rib, and a leading edge second rib extending from the first bulkhead generally along the second sidewall to a leading edge, the leading edge extending along both the first and second sidewalls at the leading edge. a leading edge third rib extends between the first rib and the second rib, the first rib and the second rib are aligned with each other, and the third rib is aligned with the first rib and the second rib. The feathers are staggered against each other. 15) The vane of claim 12), wherein the vane is operative to direct substantially 100% of the coolant that can flow through the first passageway to the second passageway. 16) The blade according to claim 12) has a tip and a second partition extending from the tip, the meandering passage is constituted by the second partition and the side wall, and the blade has a tip and a second partition extending from the tip; A vane having a third passage arranged substantially parallel to an edge and in flow communication with the second passage, the second passage being defined by the first and second partition walls and the side wall. 17) A vane according to claim 16), having a trailing edge opening, wherein the first and second passages transfer approximately 100% of the coolant that may flow therethrough to the second passage. and a vane that acts to send the air to the rear edge opening. 18) The blade according to claim 17, wherein the tip has a tip opening through which flow communicates with the second and third passages. 19) In a blade used in a gas turbine engine, a leading edge and a trailing edge, first and second side walls separated from each other extending between the leading edge and the trailing edge, a root, a tip, and from the root a first partition wall extending between the side walls toward the tip; and a second partition wall extending between the side walls from the tip toward the base, and the first and second partition walls are mutually connected. spaced apart from the leading edge and the trailing edge to define a serpentine coolant passageway, the serpentine coolant passageway including a first passageway extending along the leading edge, the first and second bulkheads; a second passage extending between and in flow communication with the first passage; and a second passage disposed between the second bulkhead and the trailing edge;
a third passage in flow communication with the first and second passages, said serpentine passage having a width D and a longitudinal axis, and acting to pass the coolant in a direction substantially parallel to said longitudinal axis; A plurality of substantially straight turbulent flow ribs, each of which is vertically spaced from the second side wall, are arranged substantially perpendicular to the longitudinal axis within the meandering passage, each rib having a height E. I have it, ratio E
/D is within the range of about 0.07 to about 0.333. 20) The vane of claim 19, wherein each of said first, second and third passages has a rib extending therein from said side wall. 21) In the blade according to claim 20, a rib disposed in the first passage extends along both the first and second side walls from the first partition wall to the leading edge. The feathers are growing. 22) The blade according to claim 19, wherein the ribs on the first side wall alternate with the ribs on the second side wall. 23) The vane according to claim 19), wherein a rib disposed within the first passage extends along the first sidewall from the first bulkhead generally to the leading edge. a leading edge first rib that extends; and a leading edge second rib that extends along the second sidewall from the first bulkhead to the first rib;
A blade in which the first rib and the second rib are alternated. 24) The blade according to claim 19), wherein the distance of the blade from the root to the tip is about 1 inch. 25) In the blade according to claim 19), when the height E is about 0.020 inches and the distance between the ribs in the longitudinal direction is S, the ratio S/E is about A vane that is within the range of 5.0 to about 10.0.