切油防喘系统工作时发动机推力响应
ENGINE THRUST RESPONSE TO PULSED FUEL SUPPLY IN MAIN COMBUSTOR
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摘要: 建立了某发动机切油防喘时的数学模型, 结合飞行试验所获取的数据, 计算了6种飞行条件下发动机最大工作状态下的推力变化规律, 为分析和解决有关由于防喘系统工作带来的问题提供依据, 且可为新机防喘系统设计和研制提供参考。Abstract: The mathematical model of a two spool turbojet engine with pulsed fuel supply system was established and considered in this paper.The thrust responses to pulsed fuel supply in main combustor at six flight regimes have been calculated by the use of the established model based on flight test data.The calculated results were discussed and compared with flight test data in detail.The results show that engine thrust in this case drops 77～90% in a short time.This means pulsed fuel supply system has a heavy effect on engine performance.
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