基于假设温度减推力起飞的理论依据

Principle of Assumed Temperature Reduced Thrust Takeoff

为正确使用和推广减推力起飞技术,分析了高涵道比涡轮风扇发动机温度特性和大型民航机起飞性能.假设温度是由飞机实际起飞质量确定的相当的大气温度.实施假设温度减推力起飞的必要条件是飞机实际起飞质量小于最大起飞质量,并且假设温度高于发动机推力平台温度.假设温度减推力起飞的风扇转速由发动机相似条件计算.

For correct and wide application of reduced thrust takeoff technique, the temperature characteristics of high bypass ratio turbofan engines and the takeoff performance of large aircrafts were analyzed. Assumed temperature is the equivalent ambient air temperature determined by the actual takeoff mass of an aircraft. The necessary conditions of reduced thrust takeoff are that the actual takeoff mass is less than the maximum takeoff mass of an aircraft and that the assumed temperature is higher than the reference temperature. The rotation speed of the fan under assumed temperature reduced thrust takeoff is calculated based on the analogical condition of engine.