A cooling device for the end wall of a turbine blade
A technology for cooling devices and turbine blades, which is applied in the direction of supporting components of blades, machines/engines, mechanical equipment, etc., which can solve the problems of large momentum, impact, and unsatisfactory cooling effect of cold air flowing out of slots in the vertical direction, and achieve improved Cooling efficiency, homogeneous temperature distribution, weakened interaction effect
Active Publication Date: 2022-02-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
[0003] At present, due to clearance fit upstream of the end wall, there is a gap between the outlet of the combustion chamber and the guide vane. By passing cold air through the gap, on the one hand, the intrusion of gas can be prevented, and on the other hand, the end wall can be cooled. However, due to the outflow of cold air through the slot The momentum in the vertical direction is large, and it is easily affected by the secondary flow of the cascade, which makes the cooling effect unsatisfactory
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[0017] The present invention will be further described below in conjunction with the accompanying drawings.
[0018] The invention discloses a cooling device for the end wall of a turbine vane, which comprises a cascade passage, upper and lower end walls, a slot 2, a baffle plate 3, a small guide vane 4 and a funnel-shaped groove 6. Such as figure 1 with figure 2 As shown, the gas flows in from the main inlet, flows through the cascade channel, and flows out from the outlet. There is a slot 2 between the combustion chamber and the turbine guide vane 1 because of clearance fit, and the cooling air flow introduced from the compressor flows out from the slot 2. The vane end wall 5 is cooled.
[0019] Such as image 3 As shown, there is a baffle 3 at the exit of the slot 2, the baffle 3 is fixed at the exit of the combustion chamber, the cross section is a quarter ring, the inner diameter of the ring is R1, the outer diameter is R2, and at the exit The tangent line of the gas...
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The invention discloses a cooling device for the end wall of a turbine blade, which belongs to the field of cooling and thermal protection of the end wall of the guide vane of an aero-engine and a ground gas turbine. The device includes a cascade passage, upper and lower end walls, slots, baffles, small guide vanes and funnel-shaped grooves; the cascade passage has an upper end wall and a lower end wall, and the small guide vanes are evenly arranged on the cascade In the channel, the front end of the small deflector is close to the downstream edge of the slot outlet, and there is a baffle at the slot outlet, and the upstream of the funnel-shaped groove is close to the slot outlet and is facing the leading edge of the blade. The invention can reduce the interaction between the main flow and the cold air, reduce the influence of the lateral secondary flow on the cooling of the end wall, improve the cooling efficiency of the end wall, make the temperature distribution of the end wall more uniform, and protect the end wall of the blade from ablation.
Description
technical field [0001] The invention relates to a cooling device for the end wall of a turbine blade, which belongs to the field of cooling and thermal protection of the end wall of the turbine blade of an aero-engine and a ground gas turbine. Background technique [0002] In order to improve the efficiency of aero-engines, the temperature at the outlet of the combustion chamber is getting higher and higher, but the melting point of the blade material is much lower than the temperature at the outlet of the combustion chamber. Therefore, it is particularly important to protect the blades from heat. In order to reduce NO x Most of the emissions are now premixed combustion, which makes the outlet temperature of the combustion chamber more uniform, the temperature in the middle area decreases, and the temperature near the end wall increases, and the secondary vortex device near the end wall is more complicated, which will cause The heat transfer of the end wall is affected, maki...
Claims
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IPC IPC(8): F01D5/18
CPCF01D5/18F01D5/186
Inventor 顾豪杨卫华邓创新李承阳宣文韬
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS