Turbine blade adopting small wing blade tip with cooling structure
By adopting a winglet top design with a cooling structure on the turbine blades, the leakage flow is controlled by using the suction side winglet and the blade top groove structure, the pressure loss and winglet ablation problems caused by the leakage flow of the turbine blade are solved, and the effect of improving turbine efficiency and extending the blade life is achieved.
Patent Information
- Application Number
- CN202411905893.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-23
- Publication Date
- 2025-04-25
AI Technical Summary
There is a leakage flow on the blade top of the turbine blade, which leads to an increase in pressure loss, reduces the efficiency of the gas turbine engine, and the winglet structure is prone to ablation in a high-temperature environment, shortening the service life of the blade.
The winglet leaf top design with a cooling structure is adopted, and the suction side winglet and the leaf top groove structure are used to control the flow of the leakage flow, extend the flow distance of the leakage flow, increase the flow resistance, and improve the heat transfer characteristics through the suction side air-conditioning tank to protect the winglet structure.
It effectively reduces the leakage flow on the top of the blade, increases the turbine output function, improves the turbine efficiency, and extends the service life of the blade.
Smart Images
Figure CN119878313A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a turbine, in particular to a turbine blade. Background Art
[0002] Modern gas turbine engines are mainly composed of a compressor, a combustion chamber and a turbine. When the gas passes through the compressor, it is compressed and the pressure rises. The high-pressure gas enters the combustion chamber and is fully mixed with the fuel to burn into high-temperature and high-pressure gas. Then it flows through the turbine and works on the turbine, driving the turbine's rotor to rotate. At the same time, the turbine can drive the compressor to rotate.
[0003] In the turbine rotor, a certain gap is left between the tip of the turbine blade and the outer casing wall to prevent friction between the two. There is a pressure gradient on both sides of the turbine blade. Under the action of the pressure gradient, the mainstream gas will flow through this gap from the pressure side to the suction side, forming a tip leakage flow, which then develops into a leakage vortex, increasing the total pressure loss and reducing the efficiency of the gas turbine engine.
[0004] Common leakage flow control methods include blade tip grooves and blade tip winglets, which can effectively reduce leakage losses. However, due to the high temperature and high pressure working environment and the fragility of the winglet structure, the winglet structure is easily ablated by the high temperature leakage flow, thereby reducing turbine efficiency and shortening the service life of the blades. Summary of the invention
[0005] The object of the present invention is to provide a turbine blade with a winglet tip having a cooling structure, which can reduce blade tip leakage flow, increase turbine output work and improve turbine efficiency.
[0006] The object of the present invention is achieved in that:
[0007] The present invention discloses a turbine blade with a winglet blade tip with a cooling structure, which is characterized in that it includes a blade body, the pressure side of the blade body is a pressure side wall, the suction side of the blade body is a suction side wall, at the blade tip of the blade body, the two ends of the pressure side wall and the suction side wall are respectively a blade tip leading edge and a blade tip trailing edge, a blade tip groove is provided on the blade tip, one end of the blade tip groove on the pressure side is a pressure side rib, one end of the blade tip groove on the suction side is a suction side winglet, and the suction side winglet is provided with a suction side cooling air groove.
[0008] The present invention may also include:
[0009] 1. A hollow cold air cavity is arranged inside the blade body, and the cold air cavity is connected to the suction side cold air groove.
[0010] 2. The starting point A and the ending point of the suction side winglet are located on the suction side wall, the starting point A is close to the leading edge of the blade, and the ending point B is close to the trailing edge of the blade.
[0011] 3. The thickness L of the suction side winglet is the vertical distance from the suction side wall to the outer profile line of the suction side winglet. From the starting point A of the suction side winglet to the ending point B of the suction side winglet, the thickness L of the winglet increases first and then decreases, and has a maximum thickness.
[0012] 4. The suction side winglet starts to transition from point G, the vertical vertex position of the suction side of the blade, to the blade tip of the suction side winglet. The outer wall of the suction side winglet forms an angle α with the horizontal direction. The vertical distance between point G and the blade tip is H. The outer wall of the suction side winglet forms an angle β with the top surface of the suction side winglet.
[0013] 5. The starting point C of the suction side cold air groove is located on the side of the starting point A of the suction side winglet, the ending point D of the suction side cold air groove is located on the side of the ending point B of the suction side winglet, and the width of the cold air groove is K.
[0014] 6. The suction side cooling air groove and the top of the blade cooling air cavity form an angle γ.
[0015] 7. The depth of the blade top groove is T, and the contour of the blade top groove is proportionally reduced according to the contour of the blade top.
[0016] The advantages of the present invention are as follows: the present invention utilizes the suction side winglet and the blade tip groove structure to control the flow of the leakage flow. The suction side winglet utilizes the friction between the leakage flow at the blade tip and the surrounding wall surface to extend the flow distance of the leakage flow, increase the flow resistance of the leakage flow, and thus reduce the blade tip leakage flow, increase the turbine output work, and achieve the purpose of improving the turbine efficiency. The cold air groove structure in the present invention is designed in the suction side winglet part, and the cold air protects the suction side winglet, improves the heat transfer characteristics around the blade tip, especially the suction side winglet, and extends the life of the turbine blades. At the same time, the presence of cold air can further block the flow of the leakage flow, increase the flow resistance, and thus reduce the development of the leakage vortex, and improve the efficiency of the turbine engine. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 It is a structural schematic diagram of the present invention;
[0018] Figure 2 A top view of the present invention;
[0019] Figure 3 This is the OO section view.
[0020] 1 , suction side winglet 2, suction side cold air groove 3, blade top groove 4, cold air cavity 5, pressure side wall 11, suction side wall 12, suction side winglet outer profile 13, suction side winglet outer wall surface 14, suction side winglet top surface 15, blade cold air cavity top surface 16, blade top leading edge 21, blade top trailing edge 22, suction side winglet starting point A, suction side winglet ending point B, suction side winglet thickness L, cold air groove starting point C, cold air groove ending point D, cold air groove width K, blade top groove depth T, blade suction side to suction side winglet transition point G, blade suction side to suction side winglet transition point and blade top vertical distance H, suction side winglet outer wall surface and horizontal direction angle α, suction side winglet outer wall surface and suction side winglet top surface angle β, suction side cold air groove and blade cold air cavity top angle γ. DETAILED DESCRIPTION
[0021] The present invention is described in more detail below with reference to the accompanying drawings:
[0022] Combination Figure 1-3 The present invention discloses a turbine blade with a winglet tip having a cooling structure, comprising a pressure side rib 1, a suction side winglet 2, a suction side cooling air groove 3 and a blade tip groove 4.
[0023] The starting point A and the ending point B of the suction side winglet 2 are located on the suction side wall 12 , wherein the starting point A is close to the blade leading edge 21 , and the ending point B is close to the blade trailing edge 22 .
[0024] The thickness L of the suction side winglet 2 is the vertical distance from the suction side wall 12 to the suction side winglet outer profile line 13. From the starting point A of the suction side winglet 2 to the ending point B of the suction side winglet 2, the winglet thickness L increases first and then decreases, and has a maximum thickness.
[0025] The winglet transitions from point G on the suction side 12 of the blade to the blade tip of the suction side winglet 2. The outer wall surface 14 of the suction side winglet forms an angle α with the horizontal direction. The vertical distance between point G and the blade tip is H. The outer wall surface 14 of the suction side winglet forms an angle β with the top surface 15 of the suction side winglet.
[0026] The starting point C of the suction side cold air slot 3 is close to the starting point A of the winglet, the ending point D is close to the ending point B of the winglet, and the width of the cold air slot is K.
[0027] The suction side cold air groove 3 is connected to the cold air cavity 5 inside the blade, and the suction side cold air groove 3 and the top 6 of the blade cold air cavity form an angle γ.
[0028] The blade top groove 4 has a certain depth T, and the outer contour of the groove is similar to the blade top surface profile.
Claims
1. A turbine blade with a winglet tip having a cooling structure, characterized in that: It includes a blade body, the pressure side of the blade body is the pressure side wall, the suction side of the blade body is the suction side wall, at the blade top of the blade body, the two ends of the pressure side wall and the suction side wall are the blade top leading edge and the blade top trailing edge respectively, a blade top groove is opened on the blade top, the pressure side end of the blade top groove is the pressure side rib, the suction side end of the blade top groove is the suction side winglet, and the suction side winglet is opened with a suction side cooling air groove.
2. The turbine blade with a winglet tip having a cooling structure according to claim 1, characterized in that: A hollow cold air cavity is arranged inside the blade body, and the cold air cavity is connected to the suction side cold air groove.
3. The turbine blade with a winglet tip having a cooling structure according to claim 1, characterized in that: The starting point A and the ending point of the suction side winglet are located on the suction side wall, the starting point A is close to the leading edge of the blade, and the ending point B is close to the trailing edge of the blade.
4. The turbine blade with a winglet tip having a cooling structure according to claim 3 is characterized in that: The thickness L of the suction side winglet is the vertical distance from the suction side wall to the outer profile line of the suction side winglet. From the starting point A of the suction side winglet to the ending point B of the suction side winglet, the winglet thickness L increases first and then decreases and has a maximum thickness.
5. The turbine blade with a winglet tip having a cooling structure according to claim 1, characterized in that: The suction side winglet transitions from point G, the apex position on the suction side of the blade in the vertical direction, to the blade tip of the suction side winglet. The outer wall of the suction side winglet forms an angle α with the horizontal direction. The vertical distance between point G and the blade tip is H. The outer wall of the suction side winglet forms an angle β with the top surface of the suction side winglet.
6. The turbine blade with a winglet tip having a cooling structure according to claim 2, characterized in that: The starting point C of the suction side cold air groove is located on the side of the starting point A of the suction side winglet, the ending point D of the suction side cold air groove is located on the side of the ending point B of the suction side winglet, and the width of the cold air groove is K.
7. The turbine blade with a winglet tip having a cooling structure according to claim 2, characterized in that: The suction side cooling air groove and the cavity top of the blade cooling air cavity form an angle γ.
8. The turbine blade with a winglet tip having a cooling structure according to claim 2, characterized in that: The depth of the blade tip groove is T, and the profile of the blade tip groove is reduced in proportion to the profile of the blade tip.