To improve the confidence level of semi-physical tests for aeroengine digital control systems,the combustor back-pressure simulation study was conducted during the test process.Based on the fuel flow rate and pressure differential characteristics of the nozzle of an aeroengine combustor,a test scheme based on variable area fuel nozzle was proposed.The nozzle adopts a mechanical valve structure and is designed with a shaped hole to ensure that the pressure difference and fuel flow rate passing through the nozzle meet the test require-ments.Two variable area nozzles were manufactured and tested on a semi-physical test bench.The test results show that the main working pressure data of the digital control system in the semi-physical test is consistent with actual engine test results,thus invalidating the vari-able area fuel nozzle is a practical method for combustor back-pressure simulation.Compared with the traditional back-pressure simula-tion scheme,the variable area fuel nozzle has a simpler structure and does not need a complex combustor back-pressure control system.This test scheme are applicable to control system semi-physical tests for different engine models.
关键词
可变流通面积喷嘴/半物理模拟试验/数控系统/反压模拟/航空发动机
Key words
variable area fuel nozzle/semi-physical test/digital control system/back-pressure simulation/aeroengine
维普
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