Low-pressure turbine air cooling blade

Abstract

The invention belongs to the field of aero-engine blades, and particularly relates to a low-pressure turbine air cooling blade. The low-pressure turbine air cooling blade comprises a blade body (1), adisc tenon (2), a turbine disc (3), a front baffle (4) and a rear baffle (5). According to the low-pressure turbine air cooling blade, a fir-shaped tenon is connected with the disc tenon (2) of the low-pressure turbine disc, the blade body (1) is axially positioned through the front baffle and the rear baffle, the blade body (1) is a hollow air cooling blade body with a crown, cold air enters through a cold air inlet of the front baffle (4), passes through a cold air channel in the disc tenon and enters a cold air channel of the blade body (1) through three cold air ports in the lower surfaceof the tenon of the blade body (1), the cold air channel of the blade 1 is of a three-chamber straight channel cooling structure, and cold air flows out of a cold air outlet of the crown of the bladebody after exchanging heat with the inner wall face and is finally discharged into a main flow channel. According to the low-pressure turbine air cooling blade, flow through the cold air inlet of a disc tenon structure is smoother, the flow resistance loss is significantly reduced, airflow blockage of the cold air inlet of a trailing edge channel is effectively relieved, and the temperature of atrailing edge can be effectively lowered.

Description

technical field [0001] The application belongs to the field of aeroengine blades, in particular to a low-pressure turbine air-cooled blade. Background technique [0002] In the prior art, the air-cooled blades of the low-pressure turbine have a relatively large flow angle after the cold air enters from the cooling hole of the front baffle, and at the same time, the flow of the cold air impinges on the rear baffle and stagnates, resulting in a large pressure loss of the imported cold air, and the cold air is in the rear. After the position of the baffle is stagnant, it will block the inlet of the cold air channel at the trailing edge, resulting in the deterioration of the flow of the cold air channel at the trailing edge of the blade, the temperature of the trailing edge will increase, and the damage to the blade will be greater, which cannot meet the use requirements of the air-cooled blade of the low-pressure turbine. [0003] Therefore, it is desirable to have a technical ...

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Problems solved by technology

[0002] In the prior art, the air-cooled blades of the low-pressure turbine have a relatively large flow angle after the cold air enters from the cooling hole of the front baffle, and at the same time, the flow of the cold air impinges on the rear baffle and stagnates, resulting in a large pressure loss of the imported cold air, and the cold air is in the rear. After the position of the baffle is stagnant, it will block the inlet of the cold air channel at the trailing edge, which will lead to the deterioration of the flow of the cold air channel at the trailing edge of the blade, the temperature of the trailing edge will increase, and the damage to the blade will be greater, which cannot meet the use requirements of the air-cooled blade of the low-pressure turbine

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