Blade for improving pneumatic thermal efficiency of turbine

Abstract

The invention belongs to the field of aeroengine turbine aerodynamics and heat transfer science, and particularly relates to a blade for improving the aerodynamic thermal efficiency of a turbine. The invention discloses a blade for improving the pneumatic thermal efficiency of a turbine. Air film cooling holes are formed near the blade top of the blade top surface of a blade suction surface. And the air film cooling holes are respectively arranged at the positions of 10% and 20% of the axial chord length of the blade on the suction surface of the blade. The number of the air film cooling holes is two, and the center distance between the two air film cooling holes is 2.5% of the axial chord length of the blade at the blade top. The method has the beneficial effects that the strength and the position of a blade tip leakage vortex are controlled through different blade suction surface air film cooling hole arrangement modes (different positions, numbers and shapes of cold air holes) so as to improve the aerodynamic thermal efficiency of a turbine, the method is mainly used for reducing aerodynamic loss caused by the blade tip leakage vortex, meanwhile, the thermal load of the blade suction surface is reduced, and the efficiency of the turbine is improved. And the working life of the turbine is prolonged.

Description

technical field [0001] The invention belongs to the field of aeroengine turbine aerodynamics and heat transfer, and in particular relates to a blade for improving the aerodynamic thermal efficiency of the turbine. Background technique [0002] Unshrouded high-pressure turbine blades will generate tip leakage flow under the action of pressure difference on both sides of the tip. In the field of turbine aerodynamics and heat transfer research, this part of the fluid will cause negative effects in two aspects: blade work loss and heat load increase. When the blade tip clearance increases by 1% of the blade height, the turbine stage efficiency will decrease by about 1%-3%. At present, it is known that in general, the loss caused by the tip leakage flow accounts for about 30% of the total loss of the turbine. When the blade design develops towards high performance and high load, the tip leakage flow will have a negative impact on the turbine efficiency, so the research on the c...

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Problems solved by technology

[0004] However, since the flow velocity on the suction side of the blade is higher than that on the pressure side, it is generally believed that if the air film cooling holes are arranged, the flow field will be disturbed and the aerodynamic loss will increase. Therefore, the air film cooling holes are usually avoided or reduced on the suction side of the blade.

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