Aerodynamic-thermal compound optimization structure of double-rake misaligned opening type of turbine blade with crown
By setting circumferentially staggered slots on the double grates of the crowned turbine blades, the mixing loss between the leakage flow and the mainstream and the thermal load of the grates are optimized, solving the problems of high mixing loss and high thermal load in the prior art and reducing the manufacturing difficulty of the cooling structure.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHANGHAI JIAOTONG UNIV
- Filing Date
- 2025-09-25
- Publication Date
- 2026-07-21
AI Technical Summary
The leakage flow between the grates and the casing of existing crowned turbine blades is deflected at a large angle from the mainstream, resulting in high mixing losses. Furthermore, the grates are located in a high heat load region, which is difficult for existing cooling structures to effectively cover.
The design incorporates a double-grate staggered open aerodynamic-thermal composite optimization structure for crowned turbine blades. By setting circumferentially staggered slots on the two grates, the mixing loss between the leakage flow and the mainstream flow is optimized, and the thermal load area of the grates is improved.
It effectively reduces leakage flow loss of crowned turbine blades and high heat load of grates, and reduces the manufacturing difficulty of cooling structures.
Smart Images
Figure CN224532790U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to a technology in the field of aero-engine blades, in particular to a double-labyrinth misaligned opening pneumatic-thermal composite optimization structure of a shrouded turbine blade. Background Technique
[0002] The existing turbine rotor blade is of a shrouded design, and the labyrinth on the shroud is used to reduce the axial leakage flow. However, the clearance leakage flow between the labyrinth of the shrouded turbine blade and the casing has a large-angle deflection with the mainstream, which will cause high mixing loss (accounting for 15%-25% of the pneumatic loss). At the same time, the labyrinth will be impacted by the leakage flow to form a local high heat load area, and the existing cooling structure is difficult to effectively cover. Content of the Utility Model
[0003] Aiming at the deficiency that the existing labyrinth is prone to ablation and chipping in the high heat load area after being impacted by high-temperature heat flow for a long time, the utility model provides a double-labyrinth misaligned opening pneumatic-thermal composite optimization structure of a shrouded turbine blade. By setting circumferentially misaligned slits on the two labyrinths, the high mixing loss generated by the leakage flow of the shrouded turbine blade and the mainstream is reduced, and the local high heat load area generated by the labyrinth is improved, thereby reducing the manufacturing difficulty of the cooling structure.
[0004] The utility model is realized by the following technical solutions:
[0005] The utility model relates to a double-labyrinth misaligned opening pneumatic-thermal composite optimization structure of a shrouded turbine blade, including: a blade body, a part of the shroud vertically arranged thereon, and a first labyrinth and a second labyrinth arranged in parallel on the part of the shroud, wherein: a first slit is provided on the first labyrinth, and a second slit is provided on the second labyrinth.
[0006] The included angle between the opening directions of the first slit and the second slit and the axial direction satisfies < < .
[0007] The height h of the slit satisfies 0.6H < h < H, where: H is the height of the labyrinth.
[0008] The first labyrinth is located at a position on the part of the shroud close to the leading edge of the part of the shroud, and the second labyrinth is located at a position on the part of the shroud close to the trailing edge of the part of the shroud. The distance between the two labyrinths is greater than the distance between the labyrinth and the edge of the part of the shroud it is close to.
[0009] The first labyrinth and the second labyrinth are circumferentially distributed at different axial positions and are connected to the outside of the part of the shroud. Description of the Drawings
[0010] Figure 1This is a schematic structural diagram of the present utility model;
[0011] Figures 2-4 It is Figure 1 a schematic diagram of different perspectives;
[0012] In the figure: 1 High-pressure turbine blade body, 2 Partial shroud, 201 Leading edge of partial shroud, 202 Trailing edge of partial shroud, 301 First labyrinth seal, 302 Second labyrinth seal, S Circumferential length of labyrinth seal, Width of labyrinth seal tooth tip, Width of labyrinth seal tooth root, H Height of labyrinth seal, Angle of labyrinth seal tooth surface deviating from radial direction, 401 First slot, 402 Second slot, h Slot height, w Slot width, Angle of slot deviating from axial direction. Specific implementation manner
[0013] As Figures 1-4 shown, this embodiment relates to a double-labyrinth seal misaligned opening type pneumatic-thermal composite optimization structure of a shrouded turbine blade, including: blade body 1, partial shroud 2 vertically arranged thereon, and first labyrinth seal 301 and second labyrinth seal 302 arranged in parallel on partial shroud 2, wherein: first labyrinth seal 301 is provided with first slot 401, and second labyrinth seal 302 is provided with second slot 402.
[0014] The included angle between the slot directions of the first slot 401 and the second slot 402 and the axial direction satisfies < < , in this embodiment, = 60°.
[0015] The height h of the slot satisfies 0.6H < h < H. In this embodiment, h = 0.75H, where: H is the height of the labyrinth seal.
[0016] The first labyrinth seal 301 is located at a position on the partial shroud 2 close to the leading edge 201 of the partial shroud, and the second labyrinth seal 302 is located at a position on the partial shroud 2 close to the trailing edge 202 of the partial shroud. The distance between the two labyrinth seals is greater than the distance between the labyrinth seal and the edge of the partial shroud it is close to.
[0017] The width of the tooth tip of the labyrinth seal is less than the width of the tooth root .
[0018] The angle of the tooth surface of the labyrinth seal deviating from the radial direction is 5°.
[0019] The first labyrinth seal 301 and the second labyrinth seal 302 are circumferentially distributed at different axial positions and are connected to the outside of the partial shroud.
[0020] The blade 1 and part of the crown 2 are integrally cast.
[0021] Compared to existing technologies, this device effectively reduces leakage flow and lowers leakage losses through the double grates on part of the blade crown. In existing crowned turbines, the jet flow through the grates is almost axial. The first and second slots on the first and second grates reduce the mixing loss between the jet and the mainstream, while also mitigating the high heat load area caused by thermal flow impact. The circumferentially staggered grating design effectively reduces aerodynamic mixing and solves the blade crown erosion problem.
[0022] 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 crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure, characterized in that, Comprising: A blade body, a partial shroud vertically provided thereon, and first and second labyrinth teeth arranged in parallel on the partial shroud, wherein: a first slit is provided on the first labyrinth tooth, and a second slit is provided on the second labyrinth tooth.
2. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 1, characterized in that, The angle between the opening direction of the first and second slits and the axial direction satisfy < < .
3. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 1 or 2, characterized in that, The height h of the slit satisfies 0.6H < h < H, where: H is the height of the labyrinth tooth.
4. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 3, characterized in that, The first labyrinth tooth is located at a position on the partial shroud close to the leading edge of the partial shroud, and the second labyrinth tooth is located at a position on the partial shroud close to the trailing edge of the partial shroud. The distance between the two labyrinth teeth is greater than the distance between the labyrinth tooth and the edge of the partial shroud it is close to.
5. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 4, characterized in that, The first labyrinth tooth and the second labyrinth tooth are circumferentially distributed at different axial positions and are connected to the outside of the partial shroud.
6. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 1, characterized in that, The width of the tooth tip of the labyrinth tooth is smaller than the width of the tooth root.
7. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 1 or 6, characterized in that, The angle by which the tooth surface of the labyrinth tooth deviates from the radial direction is 5°.
8. The crowned turbine blade double-flanged staggered open aerodynamic-thermal composite optimized structure according to claim 1, characterized in that, The blade body and the partial shroud are integrally formed by casting.