Aero engine air compressor inner cartridge receiver with air-bleed holes and machining method thereof

Abstract

The invention relates to an aero engine air compressor inner cartridge receiver with air-bleed holes and a machining method thereof. The aero engine gas compressor inner cartridge receiver comprises an inner cartridge receiver body; a plurality of waist-shaped air-bleed holes are evenly distributed in the middle part side wall of the inner cartridge receiver body in the circumferential direction;and the air-bleed holes are for guiding an air flow moving along the inner wall of the inner cartridge receiver to divert the air flow from the positions of the air-bleed holes to the outside of an air flow passage of the air compressor inner cartridge receiver, realize inter-stage air bleeding of the air compressor and ensure that the air flow is not clogged in the air flow passage.

Description

technical field [0001] The invention relates to the technical field of aero-engine components, in particular to an aero-engine compressor inner casing with vent holes and a processing method thereof. Background technique [0002] The compressor inner casing is used in aero-engines, and is one of the important components in the compressor runner. From the development of aviation gas turbine engines in the 1920s to today, the stable operation of compressors has always been one of the focuses of aeroengine research. When the engine is working, the airflow flows out from the axial flow compressor and then enters the channel formed by the casing in the compressor and the rotor of the centrifugal compressor. At this time, the airflow velocity and pressure in the compressor further increase. The uncoordinated ratio between the rotational speed and the inhaled air flow makes the working condition of the front and rear stages of the compressor deviate from the optimum design conditi...

AI Technical Summary

Problems solved by technology

When the engine is working, the airflow flows out from the axial flow compressor and then enters the channel formed by the casing in the compressor and the rotor of the centrifugal compressor. At this time, the airflow velocity and pressure in the compressor further increase. The uncoordinated ratio between the rotational speed and the inhaled air flow makes the working conditions of the front and rear stages of the compressor deviate from the optimum design condition, thus causing the angle of attack of the blades of each stage to deviate from the optimum value, resulting in a decline in the performance of each stage, seriously When the compressor surges, it will cause the uncoordinated work of the front and rear stages of the compressor, and cause the performance of the whole machine to deteriorate. Compressor surge is a low-frequency, high-amplitude airflow oscillation phenomenon that occurs along the axis of the compressor.

Compressor surge phenomenon will lead to strong mechanical vibration of the engine and overheating of the hot end, and cause serious damage to the engine in a very short period of time. The compressor is not allowed to work in the surge region under any working conditions

If geometrical adjustment measures are not adopted, some speed performance deterioration will often occur, manifested in the local concave of the surge boundary line, the decrease of the flow rate of the characteristic line, the decrease of the pressure ratio of the surge point, and the general decrease of efficiency. Further development may cause engine surge

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