Method, system and terminal for optimizing gas compressor casing treatment to improve stability margin

Abstract

The invention belongs to the technical field of gas compressors of gas turbines for ship propulsion, and discloses a method, a system and a terminal for optimizing gas compressor casing treatment to improve the stability margin. The method for optimizing gas compressor casing treatment to improve the stability margin comprises the following steps: carrying out numerical simulation on an original casing with an axial chute and a backflow cavity and a parameter improved casing; determining the structural form of casing treatment, increasing the axial speed, adopting the whole annular air inlet and increasing the air inlet amount by adjusting an inlet of an air inlet section and enlarging the air inlet angle; and in the air outlet section, adopting an inclined shrinkage nozzle as an air outlet, increasing the outlet speed, optimizing the exhaust section, adopting the IGG / AutoGrid5 for calculation of a grid to carry out single-channel grid division, and optimizing the treatment effect of the compressor casing. According to the method, the exhaust section treatment casing can be effectively optimized, the improvement effect on the working stability margin of the gas compressor under the low working condition is the best, and the stability margin is improved by 6.04%.

Description

technical field [0001] The invention belongs to the technical field of compressors, and in particular relates to a method, a system and a terminal for optimizing the processing of a compressor casing and improving a stability margin. Background technique [0002] At present, the main function of compressor casing treatment is to reduce the flow at the stall point, thereby increasing the surge margin of the compressor. In actual work, the operating point of the compressor is approaching due to the high bleed air pressure of the APU or the change of the outlet load. The surge boundary may cause the blades of the compressor to break, or even the APU engine to stall and other serious failures. In order to improve the surge margin of the compressor, currently aero-engines mainly adopt methods such as compressor inter-stage venting and imported adjustable guide vanes. The use of interstage bleed air will cause severe fluctuations in the outlet pressure of the compressor, which is...

AI Technical Summary

Problems solved by technology

The use of inter-stage bleed air will cause severe fluctuations in the outlet pressure of the compressor, which is not suitable for APU, while the use of imported adjustable guide vanes has a complex structure, which will significantly increase the weight of the engine, and the increase in surge margin is limited

[0003] Through the above analysis, the existing problems and defects of the prior art are as follows: the casing treatment structure of the existing compressor cannot meet the demand of increasing the air intake of the compressor, and the casing of the exhaust section has a surge margin under low working conditions not tall

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