A split-flow cooled aeroengine compressor rear shaft diameter tapered wall cavity

Abstract

The invention discloses a split-cooled aeroengine compressor rear shaft diameter cone wall cavity, which is different from the traditional aeroengine air system components in which a single type of air-introduction hole is provided for air-intake cooling, but the stator cone surface and the stator drum respectively The pre-rotating nozzles with two apertures on the surface can not only realize the reasonable distribution of the cooling air flow and the reasonable configuration of the cooling parts under the condition of the total flow of the bleed air, so as to achieve precise cooling, but also shorten the flow of the cooling air in the flow channel. The flow distance can significantly reduce the wind resistance of the rotor to the cooling airflow, reduce the entropy of the airflow, improve the quality of the cold air, and can also ensure the cooling quality of the airflow out of the cone wall cavity while ensuring that the cone wall is in a comprehensive and good cooling state. The improvement of the cone wall cavity makes the downstream components get better cooling effect. The invention conforms to the low-entropy production design concept of the flow path of the air system, and can be widely used in the cooling scheme design of the air system of the advanced aeroengine.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a split-flow cooled aero-engine compressor rear shaft diameter tapered wall cavity. Background technique [0002] With the continuous improvement of aero-engine performance, the temperature before the turbine is getting higher and higher, which puts forward higher requirements for material technology and aero-engine air system cooling technology. At present, the application of aero-engine material technology has reached the extreme state. High-temperature material technology alone cannot meet all design requirements, and the remaining cooling requirements must be realized by the aero-engine air system. Normally, increasing the bleed air flow of the air system will directly improve the cooling effect of the air system, but the increase of the air system flow will lead to the decline of the overall performance of the engine. Therefore, how to reasonably distribute the cooling airflow a...

AI Technical Summary

Problems solved by technology

Therefore, the lower half of the cone wall and the components downstream of the cone wall cavity often cannot achieve a good cooling effect

[0004] Although the above-mentioned single-position bleed air cooling scheme adopted by the traditional aero-engine cone wall cavity can meet the cooling requirements of early engines, in advanced aero-engines, the temperature level is further increased, and the traditional method cannot achieve reasonable airflow. allocation and utilization, so no longer applies

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