Turbine blade and turbine engine

Abstract

The utility model relates to the technical field of turbine engines, and particularly discloses a turbine blade and a turbine engine, the turbine blade comprises a blade body, a first cooling air passage and a second cooling air passage, the blade body comprises a blade front edge, a blade middle part, a blade tail edge, a blade tip end and a blade root part; the first cooling air channel comprises a first air channel and a plurality of first air outlet holes, the first air channel comprises a first section and a second section which are communicated with each other, the first section is located at the tail edge of the blade and extends to the tip end of the blade along the root of the blade, and the first air outlet holes are formed along the first air channel at intervals; the second section is arranged in the middle of the blade, and an air inlet of the first air channel is formed in the first section; the second cooling air channel is arranged in the blade body and located at the front edge of the blade. According to the turbine blade, the cooling air channels are arranged according to different heated parts of the blade body, so that the temperatures of the parts of the blade body are uniform and effectively reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of turbine engines, in particular to turbine blades and turbine engines. Background Art

[0002] During the operation of turbine blades, especially when high-temperature gas passes through, the surface temperature can far exceed the limit working temperature of the material, resulting in a decrease in material strength, an increase in thermal stress, an acceleration of creep, and even melting failure. Therefore, effective turbine cooling blade technology is of great significance for ensuring the safe operation of the engine, extending the service life, and improving the thermal efficiency.

[0003] The cooling channels of the cooling blades in the prior art are usually radial rotary channels or S-shaped channels. The cooling air flow enters from the blade root, flows along the cooling channel and absorbs the heat of the gas. The temperature of the cooling air flow gradually increases, and the cooling capacity gradually decreases. Therefore, there is a problem that the temperature of local areas of the blade cannot be effectively reduced. Summary of the Utility Model

[0004] The purpose of the utility model is to provide turbine blades and turbine engines to solve the problem that the distribution of heat dissipation air channels in the blade in the related technology is unreasonable, and thus the temperature of local areas of the blade cannot be effectively reduced.

[0005] On the one hand, the utility model provides a turbine blade, which includes:

[0006] A blade body, which includes a blade leading edge, a blade middle part, a blade trailing edge, a blade tip and a blade root;

[0007] A first cooling air channel, which is arranged in the blade body and includes a first air channel and a plurality of first air outlet holes. The first air channel includes a first section and a second section that are communicated with each other. The first section is located at the blade trailing edge and extends from the blade root to the blade tip. The plurality of first air outlet holes are arranged at intervals in the direction from the blade root to the blade tip. One end of the first air outlet hole is communicated with the first section of the first air channel, and the other end is communicated with the outer surface of the blade trailing edge. The second section is arranged in the blade middle part, and the air inlet of the first air channel is arranged at the first section;

[0008] A second cooling air channel, which is arranged in the blade body and is located at the blade leading edge.

[0009] As a preferred technical solution of the turbine blade, the first cooling air channel further includes a confluence channel, which is arranged at the blade root. The confluence channel includes a first air inlet hole, a second air inlet hole and a confluence hole that are communicated with each other. The confluence hole is communicated with the air inlet of the first section.

[0010] As a preferred technical solution of the turbine blade, the first cooling air duct further includes a plurality of first spoiler rib columns, and the plurality of first spoiler rib columns are arranged in the first air duct and spaced along the air flow direction in the first air duct.

[0011] As a preferred technical solution of the turbine blade, the first cooling air duct further includes a plurality of second air outlet holes, one ends of the plurality of second air outlet holes are respectively communicated with the second section of the first air duct, and the other ends of the plurality of second air outlet holes are communicated with the outer surface of the middle part of the blade.

[0012] As a preferred technical solution of the turbine blade, a tip groove is recessed in the blade tip;

[0013] An air outlet is arranged in the second section of the first air duct, and the air outlet is communicated with the tip groove.

[0014] As a preferred technical solution of the turbine blade, the first air duct is arranged in an S shape.

[0015] As a preferred technical solution of the turbine blade, the second cooling air duct includes a second air duct and a plurality of third air outlet holes, the second air duct extends from the blade root to the blade tip, the plurality of third air outlet holes are spaced along the direction from the blade root to the blade tip, one end of each third air outlet hole is communicated with the second air duct, and the other end is communicated with the outer surface of the leading edge of the blade.

[0016] As a preferred technical solution of the turbine blade, the second cooling air duct further includes a plurality of second spoiler rib columns, and the plurality of second spoiler rib columns are arranged in the second air duct and spaced along the air flow direction in the second air duct.

[0017] As a preferred technical solution of the turbine blade, a supplementary air duct is further included, the supplementary air duct is arranged in the blade body, and the supplementary air duct is communicated with the second section of the first air duct.

[0018] On the other hand, the present invention provides a turbine engine, including the turbine blade in any of the above solutions.

[0019] The beneficial effects of the present invention are:

[0020] The present utility model provides a turbine blade and a turbine engine. The turbine blade includes a blade body, a first cooling air passage, and a second cooling air passage. The blade body includes a blade leading edge, a blade middle part, a blade trailing edge, a blade tip, and a blade root. The first cooling air passage is disposed within the blade body and includes a first air passage and a plurality of first air outlet holes. The first air passage includes a first section and a second section that are interconnected. The first section is located at the blade trailing edge and extends from the blade root towards the blade tip. The plurality of first air outlet holes are spaced apart in the direction from the blade root towards the blade tip. One end of each first air outlet hole is in communication with the first section of the first air passage, and the other end is in communication with the outer surface of the blade trailing edge. The second section is disposed in the blade middle part, and the air inlet of the first air passage is disposed in the first section. The second cooling air passage is disposed within the blade body and is located at the blade leading edge. When the turbine engine is operating, the blade leading edge is directly impacted by high-temperature combustion gas, which is often the area with the highest thermal load on the turbine blade. The thickness of the blade trailing edge is relatively thin, so the thermal load in this part is also relatively large. Therefore, the thermal loads of both the blade leading edge and the blade trailing edge are greater than that of the blade middle part. Since the first section of the first air passage is located at the blade trailing edge and the air inlet of the first air passage is in the first section, the cooling gas first enters the first section and then enters the second section. Therefore, after the cooling gas flows through the first section, it can dissipate heat from the blade trailing edge. At the same time, when the cooling gas flows into the second section, it can also dissipate heat from the blade middle part. Additionally, since the first air outlet connects the first section of the first air passage with the outer surface of the blade trailing edge, the gas discharged from the first air outlet can further dissipate heat from the blade trailing edge. The second cooling air passage is disposed within the blade body and is located at the blade leading edge. Therefore, the cooling gas within the second cooling air passage can independently dissipate heat from the blade leading edge. This turbine blade arranges the cooling air passages according to the thermal load conditions of each part of the blade body, thereby evenly and effectively reducing the temperatures of each part of the blade body. Description of the Drawings

[0021] Figure 1 Structural schematic diagram of the first cooling air passage, the second cooling air passage, and the supplementary air passage in an embodiment of the present utility model Figure 1 ;

[0022] Figure 2 Structural schematic diagram of the first cooling air passage, the second cooling air passage, and the supplementary air passage in an embodiment of the present utility model Figure 2 ;

[0023] Figure 3 Surface static temperature distribution nephogram of the blade body in an embodiment of the present utility model;

[0024] Figure 4 Streamline diagram of the cooling air flow in an embodiment of the present utility model;

[0025] Figure 5 Streamline diagram of the cooling air flow and the mainstream combustion gas in an embodiment of the present utility model.

[0026] In the figure:

[0027] 11. Leading edge of the blade; 12. Middle part of the blade; 13. Trailing edge of the blade; 14. Tip of the blade; 141. Tip groove; 15. Root of the blade;

[0028] 2. First cooling air duct; 21. First air duct; 211. First section; 212. Second section; 22. First air outlet; 23. Second air outlet; 24. Confluence channel; 241. First air inlet; 242. Second air inlet; 243. Confluence hole; 25. First flow disturbance rib column;

[0029] 3. Second cooling air duct; 31. Second air duct; 32. Third air outlet; 33. Second flow disturbance rib column;

[0030] 4. Supplementary air duct. Detailed implementation manners

[0031] Next, the technical solution of the present utility model will be clearly and completely described in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments in the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0032] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions. Moreover, the first feature being "above", "over" and "on" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature has a higher horizontal height than the second feature. The first feature being "below", "under" and "beneath" the second feature includes the first feature being directly below and obliquely below the second feature, or simply indicating that the first feature has a lower horizontal height than the second feature.

[0033] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0034] The embodiments of the present utility model will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are only used to explain the present utility model and should not be construed as a limitation to the present utility model.

[0035] As Figures 1 to 4 shown, this embodiment provides a turbine blade, which includes a blade body, a first cooling air passage 2, and a second cooling air passage 3. The blade body includes a blade leading edge 11, a blade middle part 12, a blade trailing edge 13, a blade tip 14, and a blade root 15. The first cooling air passage 2 is disposed inside the blade body and includes a first air passage 21 and a plurality of first air outlet holes 22. The first air passage 21 includes a first section 211 and a second section 212 that are in communication with each other. The first section 211 is located at the blade trailing edge 13 and extends from the blade root 15 towards the blade tip 14. The plurality of first air outlet holes 22 are spaced along the direction from the blade root 15 towards the blade tip 14. One end of the first air outlet hole 22 is in communication with the first section 211 of the first air passage 21, and the other end is in communication with the outer surface of the blade trailing edge 13. The second section 212 is disposed at the blade middle part 12, and the air inlet of the first air passage 21 is disposed at the first section 211. The second cooling air passage 3 is disposed inside the blade body and is located at the blade leading edge 11.

[0036] As Figure 3As shown, observing the static temperature distribution on the surface of the blade body, the highest temperature of the blade is 1162K, which is located at position 11 of the blade leading edge. The temperature at the blade trailing edge is lower than that at the blade leading edge 11 and higher than that at the blade middle part 12. When the turbine engine operates, the blade leading edge 11 is directly impacted by the high-temperature gas, and it is often the area with the largest thermal load on the turbine blade. The thickness of the blade trailing edge 13 is relatively thin. Therefore, the thermal load of this part is also relatively large, making the thermal loads of the blade leading edge 11 and the blade trailing edge 13 both larger than that of the blade middle part 12. Since the first section 211 of the first air passage 21 is located at the blade trailing edge 13 and the air inlet of the first air passage 21 is at the first section 211, the cooling gas first enters the first section 211 and then enters the second section 212. Therefore, after the cooling gas flows through the first section 211, heat dissipation of the blade trailing edge 13 can be achieved. At the same time, after the cooling gas flows into the second section 212, heat dissipation of the blade middle part 12 can also be carried out. In addition, since the first air outlet connects the first section 211 of the first air passage 21 with the outer surface of the blade trailing edge 13, the gas discharged from the first air outlet can further dissipate heat for the blade trailing edge 13. The second cooling air passage 3 is arranged inside the blade body and is located at the blade leading edge 11. Therefore, the cooling gas in the second cooling air passage 3 can achieve heat dissipation for the blade leading edge 11 alone. This turbine blade arranges the cooling air passages according to the thermal load conditions of each part of the blade body, thereby evenly and effectively reducing the temperatures of each part of the blade body.

[0037] Optionally, the first cooling air passage 2 further includes a confluence passage 24. The confluence passage 24 is arranged at the blade root 15. The confluence passage 24 includes a first air inlet hole 241, a second air inlet hole 242 and a confluence hole 243 that are connected to each other. The confluence hole 243 is connected to the air inlet of the first section 211. In this embodiment, after the cooling gas enters the first air inlet hole 241 and the second air inlet hole 242, the two cooling airflows are spirally intertwined via the confluence hole 243 and flow into the first section 211 in a direction with a pre-rotation angle. The centrifugal action increases the adhesion of the airflow to the inner surface of the first passage, which can improve the convective heat transfer coefficient and the cooling effect.

[0038] Optionally, the first cooling air passage 2 further includes a plurality of first spoiler rib columns 25. The plurality of first spoiler rib columns 25 are arranged in the first air passage 21 and are spaced along the airflow direction in the first air passage 21. In this embodiment, a plurality of first spoiler rib columns 25 are arranged in the first air passage 21, thereby increasing the turbulence of the cooling gas in the first air passage 21 and improving the convective heat transfer coefficient.

[0039] Optionally, the first cooling air duct 2 further includes a plurality of second air outlet holes 23. One ends of the plurality of second air outlet holes 23 are respectively communicated with the second section 212 of the first air duct 21, and the other ends of the plurality of second air outlet holes 23 are communicated with the outer surface of the middle part 12 of the blade. In this embodiment, the cooling gas is ejected through the second air outlet holes 23 and forms an air film at the middle part 12 of the blade. This setting can reduce the direct contact between the high-temperature combustion gas and the surface of the middle part 12 of the blade, thereby improving the temperature rise of the middle part 12 of the blade.

[0040] Optionally, the blade tip 14 is recessed with a tip groove 141; an air outlet is provided in the second section 212 of the first air duct 21, and the air outlet is communicated with the tip groove 141. In this embodiment, a part of the air flow of the cooling gas entering the first air duct 21 flows to the outer surface of the blade trailing edge 13 through the first air outlet holes 22 to cool the blade trailing edge 13 area with a smaller thickness. The remaining cold air flows out through the air outlet at the blade top and accumulates and stays in the tip groove 141 to cool the high-temperature blade tip 14. The arrangement of the tip groove 141 can reduce the scale of the tip clearance leakage vortex, thereby improving the efficiency of the turbine blade. At the same time, the inner cavity of the tip groove 141 has an accumulation effect on the cooling gas, increasing the convective heat transfer coefficient between the cooling gas in the tip groove 141 and the blade, and improving the cooling effect.

[0041] Optionally, the first air duct 21 is arranged in an S shape. In this embodiment, this setting enables the second section 212 of the first air duct 21 to cover the entire middle part 12 of the blade, and thus can effectively dissipate heat from the middle part 12 of the blade. Specifically, the first air duct 21 in this embodiment extends along the interval direction between the blade leading edge 11 and the blade trailing edge. In other embodiments, the first air duct 21 extends along the interval direction between the blade root 15 and the blade tip 14.

[0042] Optionally, the second cooling air duct 3 includes a second air duct 31 and a plurality of third air outlet holes 32. The second air duct 31 extends from the blade root 15 to the blade tip 14, and the plurality of third air outlet holes 32 are arranged at intervals in the direction from the blade root 15 to the blade tip 14. One end of each third air outlet hole 32 is communicated with the second air duct 31, and the other end is communicated with the outer surface of the blade leading edge 11. In this embodiment, after the cooling gas enters the second air duct 31, it reaches the blade leading edge 11 through the third air outlet holes 32 and forms an air film on the surface of the blade body, reducing the direct heat exchange between the combustion gas and the surface of the blade body. Observed from the suction surface side, the cooling gas flows out of the third air outlet holes 32 and then adheres to the surface of the blade body and flows to the blade trailing edge 13, with good covering performance.

[0043] Optionally, the second cooling air passage 3 further includes a plurality of second spoiler rib columns 33. The plurality of second spoiler rib columns 33 are disposed in the second air passage 31 and are spaced along the air flow direction in the second air passage 31. In this embodiment, a plurality of second spoiler rib columns 33 are arranged in the second air passage 31, thereby increasing the turbulence degree of the cooling gas in the second air passage 31 and improving the convective heat transfer coefficient.

[0044] Optionally, the turbine blade further includes a supplementary air passage 4. The supplementary air passage 4 is disposed in the blade body and is communicated with the second section 212 of the first air passage 21. In this embodiment, after the cooling gas enters from the air inlet of the first air passage 21, a part of the gas flows out from the first air outlet hole 22 and the second air outlet hole 23, and the remaining part enters the second section 212 of the first air passage 21 and finally discharges from the air outlet of the second section 212. There are two problems with the cooling gas entering the second section 212. One is the insufficient air intake, and the other is that the cooling gas carries a large amount of heat at the blade trailing edge 13. Therefore, the heat dissipation effect on the blade middle part 12 is not good. For this reason, the supplementary air passage 4 is communicated with the second section 212 of the first air passage 21. This setting can, on the one hand, supplement the cooling gas into the second section 212, and on the other hand, can reduce the temperature of the cooling gas in the second section 212, thereby improving the heat dissipation effect on the blade middle part 12.

[0045] As Figure 5 shown, regarding the mixing situation of the cooling gas and the combustion gas in the turbine flow passage, the combustion gas is not greatly affected, and the efficiency of the turbine is guaranteed. After the cooling air flow flows out of the outer surface of the blade body, it is not blown away from the outer surface of the blade body by the combustion gas in advance, ensuring the cooling effect. The percentage of the cold air flow rate in the combustion gas flow rate is 1.7%, ensuring the main combustion gas flow rate, and thus ensuring that the turbine power will not be significantly reduced.

[0046] This embodiment also provides a turbine engine, including the turbine blade in the above solution.

[0047] Obviously, the above embodiments of the present invention are merely examples for clearly explaining the present invention, rather than limiting the implementation manners of the present invention. For those of ordinary skill in the art, other different forms of changes or variations can be made based on the above description. It is not necessary and impossible to enumerate all the implementation manners here. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A turbine blade, characterized in that: include: A blade body, the blade body comprising a blade leading edge (11), a blade middle portion (12), a blade trailing edge (13), a blade tip (14) and a blade root (15); a first cooling air duct (2), arranged in the blade body, comprising a first air duct (21) and a plurality of first air outlet holes (22); the first air duct (21) comprising a first section (211) and a second section (212) which are connected to each other; the first section (211) is located at the blade trailing edge (13) and extends from the blade root (15) to the blade tip (14); the plurality of first air outlet holes (22) are arranged at intervals in a direction from the blade root (15) to the blade tip (14); one end of the first air outlet hole (22) is connected to the first section (211) of the first air duct (21), and the other end is connected to the outer surface of the blade trailing edge (13); the second section (212) is arranged in the middle of the blade (12); and the air inlet of the first air duct (21) is arranged in the first section (211); The second cooling air passage (3) is arranged in the blade body and located at the leading edge (11) of the blade.

2. The turbine blade according to claim 1, characterized in that The first cooling air duct (2) further comprises a confluence duct (24), the confluence duct (24) being arranged at the blade root (15), the confluence duct (24) comprising a first air inlet hole (241), a second air inlet hole (242) and a confluence hole (243) which are interconnected, and the confluence hole (243) is connected to the air inlet of the first section (211).

3. The turbine blade according to claim 1, characterized in that: The first cooling air duct (2) further comprises a plurality of first spoiler ribs (25), wherein the plurality of first spoiler ribs (25) are arranged in the first air duct (21) and are arranged at intervals along the airflow direction in the first air duct (21).

4. The turbine blade according to claim 1, characterized in that The first cooling air duct (2) further comprises a plurality of second air outlet holes (23), one end of each of the plurality of second air outlet holes (23) being respectively connected to the second section (212) of the first air duct (21), and the other end of each of the plurality of second air outlet holes (23) being connected to the outer surface of the middle portion (12) of the blade.

5. The turbine blade according to claim 4, characterized in that The blade tip (14) is recessed with a tip groove (141); The second section (212) of the first air channel (21) is provided with an air outlet, and the air outlet is in communication with the tip groove (141).

6. The turbine blade according to claim 1, characterized in that The first air channel (21) is arranged in an S shape.

7. The turbine blade according to any one of claims 1 to 6, characterized in that: The second cooling air duct (3) comprises a second air duct (31) and a plurality of third air outlet holes (32), wherein the second air duct (31) extends from the blade root (15) to the blade tip (14), and the plurality of third air outlet holes (32) are arranged at intervals in the direction from the blade root (15) to the blade tip (14), and one end of the third air outlet hole (32) is connected to the second air duct (31), and the other end is connected to the outer surface of the blade leading edge (11).

8. The turbine blade according to claim 7, characterized in that The second cooling air duct (3) further comprises a plurality of second spoiler ribs (33), wherein the plurality of second spoiler ribs (33) are arranged in the second air duct (31) and are arranged at intervals along the airflow direction in the second air duct (31).

9. The turbine blade according to any one of claims 1 to 6, characterized in that: It also comprises an air supply channel (4), wherein the air supply channel (4) is arranged in the blade body, and the air supply channel (4) is communicated with the second section (212) of the first air channel (21).

10. A turbine engine, characterized in that The invention comprises the turbine blade according to any one of claims 1 to 9.

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