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民机在滑跑减速阶段一般会使用发动机的反向推力来提高其减速性能和滑跑安全性,当滑跑速度较低时使用该装置,从发动机排出的向前方喷射的气流存在被发动机重新吸入的可能,该喷流受发动机风扇的压缩做功,喷流的温度比环境温度高,如果此气流被发动机重新吸入,将会导致发动机进气气流的温度畸变,而该畸变将会引起发动机风扇叶片的颤振,影响发动机的寿命和安全性。故对于一个使用涡扇发动机的新型飞机,有必要通过风洞试验来得到其在各工况下的重吸入特性,并且根据其重吸入特性,设定截止使用反推力的滑跑速度。本文主要论述通过风洞试验获得发动机重吸入特性,并且确定反推力使用截止滑跑速度的方法。
Civil aircraft in the deceleration phase of the ramp will generally use the engine reverse thrust to improve its deceleration performance and sliding safety, when the sliding speed is low when the device is used, the discharge from the engine to the front of the air jet exists by the engine to re- Inhalation may occur as a result of compression by the engine fan, the jet temperature is higher than the ambient temperature, and if this air flow is re-inhaled by the engine it will cause a temperature distortion in the engine intake air flow which will cause the engine fan Flutter of blades affects the life and safety of the engine. Therefore, for a new aircraft using a turbofan engine, it is necessary to obtain its re-intake characteristics under various operating conditions by means of wind tunnel test and to set a sliding speed of the anti-thrust force due to its re-suction characteristics. This paper mainly discusses the re-suction characteristics of the engine obtained through wind tunnel test, and determines the method of reverse thrust speed using the cut-off speed.