A method of profiling compressor blade tip region to inhibit three-dimensional corner separation

Abstract

The application discloses a kind of inhibiting three-dimensional angle area separation compressor blade end area shaping method, comprising: machine casing end wall, wheel hub end wall and stator blade, the stator blade is arranged in ring between machine casing end wall and wheel hub end wall;N layers of machine casing side laminated grooves are arranged in the connecting side of stator blade suction surface and machine casing end wall;M layers of wheel hub side laminated grooves are arranged in the connecting side of stator blade suction surface and wheel hub end wall.The machine casing side laminated groove and the wheel hub side laminated groove effectively inhibit the end wall crossflow in high load compressor due to the strong adverse pressure gradient driving to climb up along the blade suction surface end area by imitating the feather laminated structure of bird wing, avoid the end wall crossflow to form low-energy fluid mass to block the blade passage under the action of flow direction strong pressure gradient due to separation.The three-dimensional angle area separation in high load compressor is effectively inhibited by regulating blade end area flow field, the total pressure loss is reduced, and the aerodynamic performance of compressor is improved.

Description

Technical Field

[0001] This invention relates to the field of airflow control for aero-engine compressors, and more particularly to a method for shaping the end region of compressor blades to suppress three-dimensional corner separation. Background Technology

[0002] The compressor is a core component of aero-engines and a fundamental strategic industry for technologically advanced countries. With the development of modern aviation technology, the thrust-to-weight ratio requirements for aero-engines are becoming increasingly stringent. This means that compressors must increase their overall load while simultaneously reducing the number of stages to improve the load per stage. However, as compressor load levels increase, the adverse pressure gradient within the blade passages intensifies, causing low-energy fluid to accumulate towards the suction end region of the blades. This leads to the formation of three-dimensional corner separation flow, which blocks the blade passages and severely degrades the compressor's aerodynamic performance. Under high load conditions, this three-dimensional corner separation flow further evolves into three-dimensional corner stall flow, and even develops into large-scale separation flow covering the entire blade height passage, resulting in a sharp decline in compressor performance and significantly impacting the compressor's pressure ratio, efficiency, and margin. To control the three-dimensional corner separation flow in compressors, various flow control methods have been introduced. Active control methods offer good regulation results but require additional energy, limiting their application in engineering. Passive control methods often perform well under specific operating conditions but are difficult to apply broadly across a wide range of operating conditions.

[0003] To address the issue of crossflow rising along the suction surface end region of compressor blades under strong adverse pressure gradients in high-load compressors, where separation occurs due to the strong pressure gradient in the flow direction, resulting in low-energy fluid masses that clog the blade passages, reduce the flow capacity of the blade passages, and cause significant total pressure loss, this invention proposes a compressor blade end region shaping method to suppress three-dimensional corner separation. By shaping the suction surface end region of the compressor blades, the method effectively suppresses three-dimensional corner separation and improves the aerodynamic performance of high-load compressors. Summary of the Invention

[0004] (a) Technical problems to be solved

[0005] The purpose of this invention is to provide a method for shaping the end region of compressor blades to suppress three-dimensional corner separation. By mimicking the layered structure of bird feathers, the end region of the suction surface of the blade is shaped to suppress the upward rise of the endwall crossflow driven by the strong reverse pressure gradient along the end region of the blade suction surface in high-load compressors. This prevents separation caused by the strong pressure gradient in the flow direction, which leads to the formation of low-energy fluid masses that block the blade passage, reduce the flow capacity of the blade passage, and cause a strong total pressure loss problem.

[0006] (II) Technical Solution

[0007] To address the aforementioned technical problems, this invention provides a compressor blade end region shaping method for suppressing three-dimensional corner separation, comprising a casing end wall, a hub end wall, and stator blades, wherein the stator blades are arranged in a ring between the casing end wall and the hub end wall; the stator blades include a stator blade suction surface, a stator blade pressure surface, a stator blade leading edge, and a stator blade trailing edge.

[0008] On the side where the stator blade suction surface connects to the casing end wall, n layers of casing-side stacked grooves are arranged. These casing-side stacked grooves are sequentially numbered from the casing end wall to the stator blade suction surface along the blade center direction as casing-side stacked groove 1, casing-side stacked groove i, and casing-side stacked groove n. Here, i represents the number of the casing-side stacked groove, which is a positive integer between 0 and n. n represents the total number of casing-side stacked grooves, which is a positive integer between 0 and 20. The height of the junction between the casing-side stacked groove n and the stator blade suction surface does not exceed 30% of the stator blade's spanwise height.

[0009] The casing-side stacked groove has a starting end face perpendicular to the suction surface of the stator blade; the starting end face of the casing-side stacked groove 1 is located at the starting position of the three-dimensional angle separation on the suction surface side of the stator blade on the casing side; the starting end face of the casing-side stacked groove n is located before the trailing edge of the stator blade; the starting end face of the casing-side stacked groove i is located between the starting end face of the casing-side stacked groove 1 and the starting end face of the casing-side stacked groove n, and the position of the starting end face of the casing-side stacked groove i increases uniformly with the increase of i; the depth of the starting end face of the casing-side stacked groove i decreases uniformly with the increase of i, and the maximum depth does not exceed one-quarter of the maximum thickness of the stator blade.

[0010] The casing-side stacked groove has the same profile as the stator blade suction surface at the same height. Specifically, the profile of the stator blade suction surface is cut off at the starting end face of the casing-side stacked groove i and offset towards the stator blade pressure surface by the same depth as the starting end face of the casing-side stacked groove i, thus obtaining the profile of the casing-side stacked groove i. A chamfer is drawn at the intersection of the profile of the casing-side stacked groove i and the profile of the stator blade pressure surface to form the tail edge of the casing-side stacked groove i. The starting end face of the casing-side stacked groove i and the profile of the casing-side stacked groove i together constitute the geometry of the casing-side stacked groove i.

[0011] A set of m layers of hub-side stacked grooves is arranged on the side where the stator blade suction surface connects to the hub end wall. These hub-side stacked grooves are sequentially numbered from the hub end wall to the stator blade suction surface along the blade center direction as hub-side stacked groove 1, hub-side stacked groove j, and hub-side stacked groove m. Here, i represents the number of the hub-side stacked grooves, and its value is a positive integer between 0 and m. m represents the total number of hub-side stacked grooves, and its value is a positive integer between 0 and 20. The height of the junction between the hub-side stacked groove m and the stator blade suction surface does not exceed 30% of the stator blade's spanwise height.

[0012] The hub-side stacked groove has a starting end face perpendicular to the suction surface of the stator blade; the starting end face of the hub-side stacked groove 1 is located at the starting position of the three-dimensional angle separation on the suction surface side of the stator blade on the hub side; the starting end face of the hub-side stacked groove m is located before the trailing edge of the stator blade; the starting end face of the hub-side stacked groove j is located between the starting end face of the hub-side stacked groove 1 and the starting end face of the hub-side stacked groove m, and the position of the starting end face of the hub-side stacked groove j increases uniformly with the increase of j; the depth of the starting end face of the hub-side stacked groove j decreases uniformly with the increase of j, and the maximum depth does not exceed one-quarter of the maximum thickness of the stator blade.

[0013] The hub-side stacked groove has the same profile as the stator blade suction surface at the same height. Specifically, the profile of the stator blade suction surface is cut off at the starting end face of the hub-side stacked groove j and offset towards the stator blade pressure surface by the same depth as the starting end face of the hub-side stacked groove j, thus obtaining the profile of the hub-side stacked groove j. A chamfer is drawn at the intersection of the profile of the hub-side stacked groove j and the profile of the stator blade pressure surface to form the tail edge of the hub-side stacked groove j. The starting end face of the hub-side stacked groove j and the profile of the hub-side stacked groove j together constitute the geometry of the hub-side stacked groove j.

[0014] Specifically, the stacked grooves on the casing side and the stacked grooves on the hub side can be provided separately; when the total number n of the stacked grooves on the casing side is 0, no stacked grooves are provided on the casing side; when the total number n of the stacked grooves on the casing side is a positive integer between 1 and 20, stacked grooves are provided on the casing side; when the total number m of the stacked grooves on the hub side is 0, no stacked grooves are provided on the hub side; when the total number m of the stacked grooves on the hub side is a positive integer between 1 and 20, stacked grooves are provided on the hub side.

[0015] (III) Beneficial Effects

[0016] The compressor blade end-area shaping method for suppressing three-dimensional corner separation provided by the present invention has the following beneficial effects: by imitating the layered structure of bird feathers, the end-area of ​​the blade suction surface is shaped, and the layered grooves on the casing side / hub side effectively suppress the end-wall crossflow generated by the strong reverse pressure gradient in the high-load compressor from climbing upward along the end-area of ​​the blade suction surface, and avoid the end-wall crossflow from separating under the action of the strong pressure gradient in the flow direction to form a low-energy fluid mass that blocks the blade channel.

[0017] The compressor blade end-area shaping method provided by this invention effectively suppresses three-dimensional corner separation in high-load compressors by regulating the flow field in the blade end-area, improving the flow capacity of the blade channel, reducing total pressure loss, and thus improving the aerodynamic performance of the compressor. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the suction surface of the blade passage in a compressor blade end region shaping method for suppressing three-dimensional corner separation according to the present invention.

[0019] Figure 2 This is a schematic diagram of the pressure surface of the blade passage in a compressor blade end region shaping method for suppressing three-dimensional corner region separation according to the present invention;

[0020] Figure 3 This is a diagonal side view of a single stator blade in a compressor blade end region shaping method for suppressing three-dimensional corner region separation according to the present invention.

[0021] Figure 4 This is a cross-sectional view of a compressor blade with stacked grooves n on the casing side, which is part of the compressor blade end region shaping method for suppressing three-dimensional corner separation according to the present invention.

[0022] Figure 5 This is a front view of a compressor blade with stacked grooves on the casing side and hub side, representing a method for shaping the end region of a compressor blade to suppress three-dimensional corner separation according to the present invention.

[0023] In the figure, 1: casing end wall; 2: hub end wall; 3: stator blade; 4: stator blade suction surface; 5: stator blade pressure surface; 6: stator blade leading edge; 7: stator blade trailing edge; 8: casing side stacked groove; 9: casing side stacked groove 1; 10: casing side stacked groove i; 11: casing side stacked groove n; 12: casing side stacked groove starting end face; 13: casing side stacked groove profile; 14: casing side stacked groove i profile; 15: hub side stacked groove; 16: hub side stacked groove 1; 17: hub side stacked groove j; 18: hub side stacked groove m; 19: hub side stacked groove starting end face; 20: hub side stacked groove profile; 21: hub side stacked groove j profile. Detailed Implementation

[0024] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0025] like Figure 1 As shown, the present invention provides a method for shaping the end region of a compressor blade to suppress three-dimensional corner separation, comprising: a casing end wall (1), a hub end wall (2), and a stator blade (3), wherein the stator blade (3) is arranged in a ring between the casing end wall (1) and the hub end wall (2); the stator blade (3) includes a stator blade suction surface (4), a stator blade pressure surface (5), a stator blade leading edge (6), and a stator blade trailing edge (7).

[0026] n layers of casing-side stacked grooves (8) are arranged on the side where the stator blade suction surface (4) connects to the casing end wall (1). The casing-side stacked grooves (8) are numbered sequentially from the casing end wall (1) to the stator blade suction surface (4) in the blade direction as casing-side stacked groove 1 (9), casing-side stacked groove i (10), and casing-side stacked groove n (11). i represents the number of the casing-side stacked groove (8), and its value is a positive integer between 0 and n. n represents the total number of casing-side stacked grooves (8), and its value is a positive integer between 0 and 20. The height of the junction between the casing-side stacked groove n (11) and the stator blade suction surface (4) does not exceed 30% of the spanwise height of the stator blade (3).

[0027] The casing-side stacked groove (8) has a casing-side stacked groove starting end face (12) perpendicular to the stator blade suction surface (4); the starting end face of the casing-side stacked groove 1 (9) is located at the starting position of the three-dimensional corner separation on the side of the casing-side stator blade suction surface (4); the starting end face of the casing-side stacked groove n (11) is located in front of the stator blade trailing edge (7); the starting end face of the casing-side stacked groove i (10) is located between the starting end face of the casing-side stacked groove 1 (9) and the starting end face of the casing-side stacked groove n (11), and the position of the starting end face of the casing-side stacked groove i (10) increases uniformly with the increase of i; the depth of the starting end face of the casing-side stacked groove i (10) decreases uniformly with the increase of i, and the maximum depth does not exceed one-quarter of the maximum thickness of the stator blade (3).

[0028] The casing-side stacked groove (8) has the same profile as the stator blade suction surface (4) at the same height. Specifically, the profile of the stator blade suction surface (4) is cut off at the starting end face of the casing-side stacked groove i ((10)) and offset towards the stator blade pressure surface (5) by the same depth as the starting end face of the casing-side stacked groove i ((10)) to obtain the casing-side stacked groove i profile (14). A chamfer is drawn at the intersection of the casing-side stacked groove i profile (14) and the stator blade pressure surface (5) to form the tail edge of the casing-side stacked groove i (10). The starting end face of the casing-side stacked groove i (10) and the casing-side stacked groove i profile (14) together constitute the geometry of the casing-side stacked groove i (10).

[0029] On the side where the stator blade suction surface (4) connects to the hub end wall (2), there are m layers of hub-side stacked grooves (15). The hub-side stacked grooves (15) are numbered sequentially from the hub end wall (2) to the stator blade suction surface (4) in the blade direction as hub-side stacked groove 1 (16), hub-side stacked groove j (17), and hub-side stacked groove m (18). j represents the number of the hub-side stacked groove (15), and its value is a positive integer between 0 and m. m represents the total number of hub-side stacked grooves (15), and its value is a positive integer between 0 and 20. The height of the junction between the hub-side stacked groove m (18) and the stator blade suction surface (4) does not exceed 30% of the spanwise height of the stator blade (3).

[0030] The hub-side stacked groove (15) has a hub-side stacked groove starting end face (19) perpendicular to the stator blade suction surface (4); the starting end face of the hub-side stacked groove 1 (16) is located at the starting position of the three-dimensional corner separation on the side of the hub-side stator blade suction surface (4); the starting end face of the hub-side stacked groove m (18) is located in front of the stator blade trailing edge (7); the starting end face of the hub-side stacked groove j (17) is located between the starting end face of the hub-side stacked groove 1 (16) and the starting end face of the hub-side stacked groove m (18), and the position of the starting end face of the hub-side stacked groove j (17) increases uniformly with the increase of j; the depth of the starting end face of the hub-side stacked groove j (17) decreases uniformly with the increase of j, and the maximum depth does not exceed one-quarter of the maximum thickness of the stator blade (3).

[0031] The hub-side stacked groove (15) has the same profile as the stator blade suction surface (4) at the same height. Specifically, the profile of the stator blade suction surface (4) is cut off at the starting end face of the hub-side stacked groove j (17) and offset towards the stator blade pressure surface (5) by the same depth as the starting end face of the hub-side stacked groove j (17) to obtain the hub-side stacked groove j profile (21). A chamfer is drawn at the intersection of the hub-side stacked groove j profile (21) and the stator blade pressure surface (5) to form the tail edge of the hub-side stacked groove j (17). The starting end face of the hub-side stacked groove j (17) and the hub-side stacked groove j profile (21) together constitute the geometry of the hub-side stacked groove j (17).

[0032] Specifically, the stacked grooves (8) on the casing side and the stacked grooves (15) on the hub side can be opened separately; when the total number n of the stacked grooves (8) on the casing side is 0, no stacked grooves on the casing side are opened; when the total number n of the stacked grooves (8) on the casing side is a positive integer between 1 and 20, stacked grooves on the casing side are opened; when the total number m of the stacked grooves (15) on the hub side is 0, no stacked grooves on the hub side are opened; when the total number m of the stacked grooves (15) on the hub side is a positive integer between 1 and 20, stacked grooves on the hub side are opened.

[0033] Example 1:

[0034] Taking a high-speed, high-load compressor blade cascade studied by the research group as an example, the three-dimensional compressor blade was designed using a compressor blade end region shaping method for suppressing three-dimensional corner region separation according to the present invention.

[0035] like Figure 3The image shows a single stator blade in a compressor blade end region shaping method for suppressing three-dimensional corner separation according to the present invention. In this embodiment, three layers of casing-side stacked grooves (8) are arranged on the side where the stator blade suction surface (4) connects to the casing end wall (1). The casing-side stacked grooves (8) are sequentially numbered as casing-side stacked groove 1 (9), casing-side stacked groove 2, and casing-side stacked groove 3 in the blade mid-direction from the casing end wall (1) to the stator blade suction surface (4). The height of the junction between the casing-side stacked groove 3 and the stator blade suction surface (4) accounts for 15% of the spanwise height of the stator blade (3).

[0036] The relative chord length of the starting end face of the stacked groove 1 (9) on the casing side is 30%; the relative chord length of the starting end face of the stacked groove 2 on the casing side is 33%; and the relative chord length of the starting end face of the stacked groove 3 on the casing side is 36%.

[0037] The casing-side stacked groove (8) has the same profile as the stator blade suction surface (4) at the same height. Specifically, the profile of the stator blade suction surface (4) is cut off from the starting end face of the casing-side stacked groove 1 (9) and offset towards the stator blade pressure surface (5) by 25% of the maximum thickness of the stator blade (3), thus obtaining the profile of the casing-side stacked groove 1. A chamfer is drawn at the intersection of the stator blade pressure surface (5) and the profile of the casing-side stacked groove 1 to form the tail edge of the casing-side stacked groove 1. The profile of the stator blade suction surface (4) is cut off from the starting end face of the casing-side stacked groove 2 and offset towards the stator blade pressure surface (5). Laterally offset by 22% of the maximum thickness of the stator blade (3), the casing-side stacked groove 2 profile is obtained, and a chamfer is drawn at the intersection of the stator blade pressure surface (5) and the casing-side stacked groove 2 profile to form the tail edge of the casing-side stacked groove 2; the profile of the stator blade suction surface (4) is cut off from the starting end face of the casing-side stacked groove 3 and offset towards the stator blade pressure surface (5) by 19% of the maximum thickness of the stator blade (3), the casing-side stacked groove 3 profile is obtained, and a chamfer is drawn at the intersection of the stator blade pressure surface (5) and the casing-side stacked groove 3 profile to form the tail edge of the casing-side stacked groove 3.

[0038] To avoid excessive offset from significantly affecting the stiffness and aerodynamic performance of the stator blade (3), the maximum offset of the stacked groove 1 profile on the casing side shall not exceed one-quarter of the maximum thickness of the stator blade (3).

[0039] Three layers of hub-side stacked grooves (15) are arranged on the side where the stator blade suction surface (4) connects to the hub end wall (2). The hub-side stacked grooves (15) are numbered sequentially from the hub end wall (2) to the stator blade suction surface (4) in the blade direction as hub-side stacked groove 1 (16), hub-side stacked groove 2, and hub-side stacked groove 3. The height of the junction between the hub-side stacked groove 3 and the stator blade suction surface (4) accounts for 15% of the spanwise height of the stator blade (3).

[0040] The relative chord length of the starting end face of the stacked groove 1 (16) on the hub side is 30%; the relative chord length of the starting end face of the stacked groove 2 on the hub side is 33%; and the relative chord length of the starting end face of the stacked groove 3 on the hub side is 36%.

[0041] The hub-side stacked groove (15) has the same profile as the stator blade suction surface (4) at the same height; specifically, the profile of the stator blade suction surface (4) is cut off from the starting end face of the hub-side stacked groove 1 (16) and offset towards the stator blade pressure surface (5) by 25% of the maximum thickness of the stator blade (3), thus obtaining the profile of the hub-side stacked groove 1. A chamfer is drawn at the intersection of the stator blade pressure surface (5) and the hub-side stacked groove 1 to form the tail edge of the hub-side stacked groove 1; the profile of the stator blade suction surface (4) is cut off from the starting end face of the hub-side stacked groove 2 and offset towards the stator blade pressure surface (5) by 25% of the maximum thickness of the stator blade (3), thus obtaining the profile of the hub-side stacked groove 1. The stator blade (3) is offset to the side by 22% of the maximum thickness of the stator blade (3) to obtain the hub-side stacked groove 2 profile. A chamfer is drawn at the intersection of the stator blade pressure surface (5) and the hub-side stacked groove 2 profile to form the tail edge of the hub-side stacked groove 2. The profile of the stator blade suction surface (4) is cut off from the starting end face of the hub-side stacked groove 3 and offset to the side of the stator blade pressure surface (5) by 19% of the maximum thickness of the stator blade (3) to obtain the hub-side stacked groove 3 profile. A chamfer is drawn at the intersection of the stator blade pressure surface (5) and the hub-side stacked groove 3 profile to form the tail edge of the hub-side stacked groove 3.

[0042] To avoid excessive offset from significantly affecting the stiffness and aerodynamic performance of the stator blade (3), the maximum offset of the stacked groove 1 profile on the hub side shall not exceed one-quarter of the maximum thickness of the stator blade (3).

[0043] Numerical verification results show that the compressor blade end area shaping method for suppressing three-dimensional corner separation of the present invention effectively limits the casing-side corner separation to within 15% of the blade spanwise height at the junction of the stacked groove 3 on the casing side and the stator blade suction surface (4), and effectively limits the hub-side corner separation to within 15% of the blade spanwise height at the junction of the stacked groove 3 on the hub side and the stator blade suction surface (4), thereby suppressing the development of three-dimensional corner separation on the blade suction surface side, improving the flow capacity of the blade channel, reducing the total pressure loss, and improving the compressor aerodynamic performance.

[0044] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0045] In summary, the compressor blade end-area shaping method for suppressing three-dimensional corner separation provided by this invention, by mimicking the layered structure of bird feathers, shapes the suction surface end-area of ​​the blade. The layered grooves on the casing side / hub side effectively suppress the upward movement of endwall crossflow driven by strong adverse pressure gradients along the blade suction surface end-area in high-load compressors, preventing the endwall crossflow from separating under the influence of strong pressure gradients and forming low-energy fluid masses that block the blade passages. This invention effectively suppresses three-dimensional corner separation in high-load compressors by controlling the flow field in the blade end-area, improving the flow capacity of the blade passages, reducing total pressure loss, and thus enhancing the aerodynamic performance of the compressor, demonstrating significant engineering application potential.

Claims

1. A method of profiling the tip region of a compressor blade to inhibit three-dimensional corner separation, comprising: Comprise: The machine case end wall (1), the wheel hub end wall (2) and the stator blade (3), the stator blade (3) is arranged in a ring between the machine case end wall (1) and the wheel hub end wall (2);The stator blade (3) includes stator blade suction surface (4), stator blade pressure surface (5), stator blade leading edge (6) and stator blade trailing edge (7); The stator blade suction surface (4) and the machine case end wall (1) are arranged with n layers of machine case side laminated grooves (8) on the connecting side, the machine case side laminated grooves (8) are numbered from the machine case end wall (1) to the middle direction of the stator blade suction surface (4) as machine case side laminated groove 1 (9), machine case side laminated groove i (10), machine case side laminated groove n (11);The i represents the number of machine case side laminated grooves (8), which is a positive integer between 0 and n;The n represents the total number of machine case side laminated grooves (8), which is a positive integer between 0 and 20;The height of the intersection of the machine case side laminated groove n (11) and the stator blade suction surface (4) is not more than 30% of the span height of the stator blade (3); The machine case side laminated groove (8) has a machine case side laminated groove starting end surface (12) perpendicular to the stator blade suction surface (4);The starting end surface of the machine case side laminated groove 1 (9) is located at the three-dimensional angle area separation starting position on the stator blade suction surface (4) side;The starting end surface of the machine case side laminated groove n (11) is located before the stator blade trailing edge (7);The starting end surface of the machine case side laminated groove i (10) is located between the starting end surface of the machine case side laminated groove 1 (9) and the starting end surface of the machine case side laminated groove n (11), and the position of the starting end surface of the machine case side laminated groove i (10) increases uniformly with the increase of i;The depth of the starting end surface of the machine case side laminated groove i (10) decreases uniformly with the increase of i, and the maximum depth is not more than one fourth of the maximum thickness of the stator blade (3); The machine case side laminated groove (8) has the same profile as the stator blade suction surface (4) at the same height;Specifically, the profile of the stator blade suction surface (4) is truncated at the starting end surface of the machine case side laminated groove i (10), and offset to the stator blade pressure surface (5) side by a distance equal to the depth of the starting end surface of the machine case side laminated groove i (10), to obtain the machine case side laminated groove i profile (14);An angle is drawn at the intersection of the machine case side laminated groove i profile (14) and the profile of the stator blade pressure surface (5) to form the trailing edge of the machine case side laminated groove i (10);The starting end surface of the machine case side laminated groove i (10) and the machine case side laminated groove i profile (14) jointly constitute the geometry of the machine case side laminated groove i (10). m layers of hub-side laminated grooves (15) are arranged on the side of the hub end wall (2) connecting with the static blade suction surface (4), which are sequentially numbered as hub-side laminated groove 1 (16), hub-side laminated groove j (17) and hub-side laminated groove m (18) from the hub end wall (2) to the middle direction of the static blade suction surface (4); the j represents the number of the hub-side laminated groove (15), which is a positive integer between 0 and m; the m represents the total number of the hub-side laminated groove (15), which is a positive integer between 0 and 20; the height of the intersection between the hub-side laminated groove m (18) and the static blade suction surface (4) is not more than 30% of the span height of the static blade (3); The hub-side laminated groove (15) has a hub-side laminated groove starting end face (19) perpendicular to the static blade suction surface (4); the starting end face of the hub-side laminated groove 1 (16) is located at the three-dimensional angle separation starting position on the side of the static blade suction surface (4) of the hub; the starting end face of the hub-side laminated groove m (18) is located before the static blade trailing edge (7); the starting end face of the hub-side laminated groove j (17) is located between the starting end face of the hub-side laminated groove 1 (16) and the starting end face of the hub-side laminated groove m (18), and the position of the starting end face of the hub-side laminated groove j (17) uniformly increases with the increase of j; the depth of the starting end face of the hub-side laminated groove j (17) uniformly decreases with the increase of j, and the maximum depth is not more than one fourth of the maximum thickness of the static blade (3); The hub-side laminated groove (15) has the same profile as the static blade suction surface (4) at the same height; specifically, the profile of the static blade suction surface (4) is truncated at the starting end face of the hub-side laminated groove j (17), and offset to the static blade pressure surface (5) side by a distance equal to the depth of the starting end face of the hub-side laminated groove j (17), to obtain the hub-side laminated groove j profile (21); a chamfer is drawn at the intersection between the hub-side laminated groove j profile (21) and the profile of the static blade pressure surface (5) to form the trailing edge of the hub-side laminated groove j (17); the starting end face of the hub-side laminated groove j (17) and the hub-side laminated groove j profile (21) jointly constitute the geometry of the hub-side laminated groove j (17).

2. A method of profiling the tip region of a compressor blade to suppress three-dimensional corner separation as claimed in claim 1, wherein The cassette side laminated grooves (8) and the hub side laminated grooves (15) can be respectively provided; when the total number n of the cassette side laminated grooves (8) is 0, no cassette side laminated groove is provided on the cassette side; when the total number n of the cassette side laminated grooves (8) is a positive integer between 1 and 20, the cassette side laminated grooves are provided on the cassette side; when the total number m of the hub side laminated grooves (15) is 0, no hub side laminated groove is provided on the hub side; when the total number m of the hub side laminated grooves (15) is a positive integer between 1 and 20, the hub side laminated grooves are provided on the hub side.

Images