A low-pressure turbine air-cooled blade

Abstract

The application belongs to the field of aeroengine blades, in particular to a low-pressure turbine air-cooled blade. Including: blade (1), disk tenon (2), turbine disk (3), front baffle (4) and rear baffle (5). The low-pressure turbine air-cooled blade of this application is connected to the tenon (2) of the low-pressure turbine disk through a fir tree-shaped tenon, the blade (1) is axially positioned through the front and rear baffles, and the blade (1) is a crowned hollow air-cooled blade , the cold air enters from the cold air inlet of the front baffle (4), passes through the cold air channel between the tenons, and enters the cold air channel of the blade (1) from the three cold air ports on the lower surface of the tenon of the blade (1), and the blade (1) has three cold air channels The cavity straight channel cooling structure, the cold air flows out from the cold air outlet of the blade crown after heat exchange with the inner wall surface, and finally discharged into the main channel. The air-cooled blade of the low-pressure turbine of the present application has a smoother flow of the cold air inlet of the tenon structure, significantly reduces the flow resistance loss, effectively alleviates the airflow blockage of the cold air inlet of the trailing edge channel, and can effectively reduce the temperature level of the trailing edge.

Description

Technical field [0001] The present application belongs to the field of aero engine blades, specifically involving a low-pressure turbine air-cooled blade. Background [0002] In the prior art, the low-pressure turbine air-cooled blade due to the cold air from the front baffle cooling hole after the entry of the cold air, the cold air flow angle is larger, while the cold air impact to the tailgate flow stagnation, the comprehensive result of the import air pressure loss is larger, the cold air in the tailgate position is delayed, blocking the tail edge air-conditioning channel inlet, resulting in the tail edge of the cold air channel flow deterioration, the tail edge temperature increases, the damage to the blade is larger, can not meet the use requirements of the low-pressure turbine gas-cooled blade. [0003] Therefore, it is desirable that there is a technical solution to overcome or at least mitigate at least one of the above defects of the prior art. Contents of the Inventio...

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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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