State adjustment method for performance testing of multi-stage compressor with high total pressure ratio

Abstract

The invention relates to a state adjustment method for performance testing of a multi-stage compressor with a high total pressure ratio. On the basis of combined and coordinated adjustment of four physical parameters including a compressor rotating speed, a compressor adjustable stationary guide blade angle, a tester intake throttle valve opening degree, and a tester exhaust throttle valve openingdegree, the test working state of the compressor is controlled. The working state of the compressor is controlled to be in a region near of blocking points of all equal-rotating-speed working lines to carry out speed increasing and decreasing. On the condition of multi-row stationary guide blade single adjustment, successive adjustment from back to front in a rotating speed increasing state and successive adjustment from front to back in a rotating speed decreasing state are carried out, so that the need of in-stage matching rule optimal adjustment of the compressor at a non-designing rotating speed is met. According to the invention, with reasonable utilization of the flow resistance effect of the tester intake throttle valve of the compressor, the power consumption of the compressor isreduced at the intake throttle valve; and because of combined matched adjustment with the tester exhaust throttle valve, real-time precise control of the working state of the compressor is realized.

Description

technical field [0001] The invention relates to the field of aerodynamic performance test and research of aeroengine axial flow compressor components, and is applicable to civil aircraft large bypass ratio turbofan engines with high total pressure ratio and multistage axial flow compressors carried out on the ground open air suction compressor tester. In the performance characteristic test of working condition, a state adjustment method for performance test of multi-stage compressor with high total pressure ratio is proposed. Background technique [0002] The high total pressure ratio multi-stage axial flow compressor is the core compression component of the large bypass ratio turbofan engine of civil aircraft, and its design total pressure ratio is much higher than the high pressure compressor of the military small bypass ratio turbofan engine. This type of compressor test piece has the characteristics of large driving power, high exhaust pressure and temperature, many stag...

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Problems solved by technology

Aiming at the state regulation control method of multi-stage compressor performance test with high total pressure ratio, at present, no detailed elaboration of relevant content information has been found through technical novelty search, literature search, etc.

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