High-pressure turbine blade with rib wall winglet combination

Abstract

A pressure side rib wall is arranged on the side, close to the tip end face, of the pressure face of the high-pressure turbine blade, a suction side tail-cut winglet is arranged on the side, close to the tip end face, of the suction face, and the pressure side rib wall and the suction side tail-cut winglet form a groove located in a blade tip. The inclined rib wall on the pressure side is used for preventing fluid from entering the gap, meanwhile, the suction side tail cut winglet of an improved structure is adopted, formation and development of leakage vortexes can be controlled, a high-heat load area at the tail edge of the suction surface can be improved, cooling holes are formed in the bottom of the groove to effectively cool the blade top, and therefore the purposes of reducing leakage loss and improving the service life of the blade are achieved. And the heat exchange performance of the blade tip is improved.

Description

Technical Field

[0001] This utility model relates to a technology in the field of aero-engines, specifically a high-pressure turbine blade with ribbed winglets. Background Technology

[0002] As one of the three core components of an aero-engine, the turbine directly affects its performance. Due to the radial pressure difference between the rotating turbine blades and the stationary casing, some high-temperature fluid flows through the gap, causing aerodynamic losses and blade tip erosion within the flow channel. To reduce leakage flow, much research has been conducted on blade tip structures. Existing blade tip structures can reduce gap leakage flow to some extent, but their control effect and reduction of blade tip thermal load are not ideal. Utility Model Content

[0003] To address the aforementioned shortcomings of existing technologies, this invention proposes a high-pressure turbine blade with a combination of ribs and winglets. The inclined ribs on the pressure side impede fluid entry into the gap, while the improved suction-side tail-cut winglets not only control the formation and development of leakage vortices but also improve the high heat load area at the trailing edge of the suction surface. Furthermore, cooling holes are arranged at the bottom of the groove to effectively cool the blade tip, thereby reducing leakage losses and improving the heat transfer performance of the blade tip.

[0004] This utility model is achieved through the following technical solution:

[0005] This utility model relates to a high-pressure turbine blade with a combination of ribs and winglets. The pressure side is provided with a pressure side rib on the side near the blade tip, and the suction side is provided with a suction side tail winglet on the side near the blade tip. The pressure side rib and the suction side tail winglet form a groove on the blade tip.

[0006] The groove is provided with four cooling holes, and the center positions of the four cooling holes and the axial chord distances satisfy the following: the center of the first cooling hole is located at 20% of the axial chord distance from the leading edge, the center of the second cooling hole is located at 40% of the axial chord distance from the leading edge, the center of the third cooling hole is located at 60% of the axial chord distance from the leading edge, and the center of the fourth cooling hole is located at 70% of the axial chord distance from the leading edge.

[0007] The rib width s of the pressure-side rib wall is equal everywhere from the leading edge to the trailing edge. Where: h is the rib height.

[0008] The pressure-side rib wall is inclined from 20% to 85% of the distance from the leading edge point, meaning that the portion of the pressure-side rib wall that is in the plane of the groove is shifted into the groove by a rib width *s*, with an inclination angle of...

[0009] The width of the suction-side tail clipping wing increases and then decreases from the starting point to the ending point, reaching its maximum width at 70% of the axial chord length from the leading edge.

[0010] The starting point of the suction-side tail clipping winglet and the connection point of the blade suction surface are smoothly transitioned by a spline curve, and the ending point of the suction-side tail clipping winglet and the inner contour line of the rib wall are right-angled. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the structure of this utility model;

[0012] Figure 2 for Figure 1 Cross-sectional view of the blade tip rib and winglet combined configuration along the AA line;

[0013] Figure 3 This is a schematic diagram of the cooling hole layout at the bottom of the blade tip groove of this utility model;

[0014] In the figure: 1 Pressure surface, 2 Suction surface, 3 Pressure side rib wall, 4 Suction side tail clipping wing, 5 Groove, 6 Leading edge point, 7 Trailing edge point, 8 Casing, 9 Mid-arc line at the bottom of the groove, s Width of pressure side rib wall, w Width of suction side tail clipping wing, h Rib height, α Inclination angle of pressure rib wall, 101 First cooling hole, 102 Second cooling hole, 103 Third cooling hole, 104 Fourth cooling hole, Cx Axial chord length, A Starting point of suction side tail clipping wing, B Ending point of suction side tail clipping wing. Detailed Implementation

[0015] like Figures 1-3 As shown, this embodiment relates to a high-pressure turbine blade with a combination of ribs and winglets. The pressure surface 1 has a pressure side rib 3 on the side near the blade tip, and the suction surface 2 has a suction side tail winglet 4 on the side near the blade tip. The pressure side rib 3 and the suction side tail winglet 4 form a groove 5 located on the blade tip.

[0016] The groove 5 is provided with four cooling holes, and the center positions of the four cooling holes and the axial chord distances satisfy the following: the center of the first cooling hole 101 is located at 20% of the axial chord distance from the leading edge point 6, the center of the second cooling hole 102 is located at 40% of the axial chord distance from the leading edge point 6, the center of the third cooling hole 103 is located at 60% of the axial chord distance from the leading edge point 6, and the center of the fourth cooling hole 104 is located at 70% of the axial chord distance from the leading edge point 6.

[0017] The diameter of the second cooling hole 102 is set to 1.7 times the diameter of the other three cooling holes. For different blade shapes and operating conditions, the layout and parameters of the cooling holes need to be adjusted.

[0018] The rib width s of the pressure-side rib wall 3 is equal everywhere from the front edge to the tail edge. Where: h is the rib height.

[0019] The pressure-side rib 3 is inclined from 20% to 85% of the distance from the leading edge point 6, and the portion of the pressure-side rib 3 and the plane containing the groove 5 is shifted into the groove by a rib width s, with an inclination angle of... The preferred range is 50° to 65°.

[0020] The suction-side tail clipping wing 4 starts at point A on the suction surface 2, and is k times the axial chord length away from the leading edge point 6, where k ∈ (10%, 20%); the suction-side tail clipping wing 4 ends at point B, and is j times the axial chord length away from the trailing edge point 7, where j ∈ [20%, 30%).

[0021] The width w of the suction-force side tail clipper 4 increases and then decreases from the starting point A to the ending point B, reaching its maximum width w at 70% of the axial chord length from the leading edge point 6. max .

[0022] The maximum width w max Preferably, it is 3 times the rib width s.

[0023] The pressure side rib 3 at a position of 20% to 85% smoothly transitions with the inner profile of the groove 5 as a spline curve.

[0024] The starting point A of the suction-side tail clipping wing 4 and the connection between the blade suction surface 2 are smoothly transitioned by a spline curve, and the ending point B of the suction-side tail clipping wing 4 and the inner contour line of the rib wall are right-angled.

[0025] This device employs an inclined design for the pressure-side ribs, which are then translated into a groove. The resulting concave surface guides the fluid in the blade tip pressure region along the inclined ribs from the leading edge to the trailing edge, effectively preventing leakage flow from the blade tip into the gap. Furthermore, the initial inclination of the pressure-side ribs causes some flow separation, effectively reducing leakage flow. A suction-side tail-cut wing is installed on the blade tip suction surface. Firstly, the wing alters the flow path of the leakage flow, controlling the generation and development of leakage vortices. Secondly, the tail section of the wing guides the fluid in the groove out through the opening, reducing mixing between the leakage flow and the mainstream, thus lowering leakage losses. Simultaneously, a layout of four cooling holes along the mid-arc line is used. The center position of the cooling holes is determined by the axial chord distance. For cooling the suction-side tail-cut wing structure, increasing the diameter of the second cooling hole helps reduce the heat transfer coefficient between the bottom of the blade tip leading edge groove and the surface of the suction-side tail-cut wing.

[0026] The above-described specific implementations can be partially adjusted by those skilled in the art in different ways without departing from the principles and purpose of this utility model. The scope of protection of this utility model is determined by the claims and is not limited to the above-described specific implementations. All implementation schemes within its scope are bound by this utility model.

Claims

1. A high-pressure turbine blade with ribbed airfoils, characterized in that, The pressure surface has a pressure side rib wall on the side near the blade tip, and the suction surface has a suction side tail clipping wing on the side near the blade tip. The pressure side rib wall and the suction side tail clipping wing form a groove on the blade tip. The starting point of the suction-side tail clipping wing is located on the suction surface, at a distance of k times the axial chord length from the leading edge, k∈(10%,20%); the ending point of the suction-side tail clipping wing is at a distance of j times the axial chord length from the trailing edge, j∈[20%,30%). The width of the suction-side tail clipping wing first increases and then decreases from the starting point to the ending point, reaching its maximum width at 70% of the axial chord length from the leading edge.

2. The high-pressure turbine blade with ribbed airfoil assembly according to claim 1, characterized in that, The groove is provided with four cooling holes.

3. The high-pressure turbine blade with ribbed airfoil assembly according to claim 2, characterized in that, The center positions of the four cooling holes satisfy the following relationships with the axial chord length: the center of the first cooling hole is located at 20% of the axial chord length from the leading edge, the center of the second cooling hole is located at 40% of the axial chord length from the leading edge, the center of the third cooling hole is located at 60% of the axial chord length from the leading edge, and the center of the fourth cooling hole is located at 70% of the axial chord length from the leading edge.

4. The high-pressure turbine blade with ribbed airfoil assembly according to claim 3, characterized in that, The diameter of the second cooling hole is set to 1.7 times the diameter of the other three cooling holes.

5. The high-pressure turbine blade with ribbed airfoil assembly according to claim 1, characterized in that, The rib width s of the pressure-side rib wall is equal everywhere from the leading edge to the trailing edge, s= h, where h is the rib height.

6. The high-pressure turbine blade with ribbed airfoil assembly according to claim 1 or 5, characterized in that, The pressure-side rib wall is inclined from 20% to 85% of the distance from the leading edge point, meaning that the portion of the pressure-side rib wall that is in the plane of the groove is shifted into the groove by a rib width *s*, with an inclination angle of... .

7. The high-pressure turbine blade with ribbed airfoil assembly according to claim 1 or 5, characterized in that, The pressure side rib wall at the 20% to 85% position smoothly transitions with the inner profile of the groove as a spline curve.

8. The high-pressure turbine blade with ribbed airfoil assembly according to claim 1, characterized in that, The starting point of the suction-side tail clipping winglet and the connection point of the blade suction surface are smoothly transitioned by a spline curve, and the ending point of the suction-side tail clipping winglet and the inner contour line of the rib wall are right-angled.

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