喷管喉道面积变化对大涵道比分排涡扇发动机性能的影响  

Effect of Nozzle Throat Area Variation on Performance of High Bypass Ratio Turbofan Engine with Separate Flow

作　　者：唐宇峰[1] 沈锡钢[1] 李泳凡[1] 李瑞军[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2011年第1期12-15,19,共5页Aeroengine

摘　　要：使用Gasturb软件计算和分析了大涵道比分排涡扇发动机内、外涵喷管喉道面积变化对发动机性能的影响。在低压转子换算转速一定的控制规律下,研究了某型发动机喷管喉道面积变化对发动机转差、裕度、涡轮进口温度、推力、耗油率的影响。经过对比这些相互关系,可以得到1个最合理的内、外涵的喷管面积,从而指导用户最大限度地优化发动机的性能和延长发动机的使用寿命。The effect of core and bypass throat area variation on the performance of high bypass ratio turbofan engine with separate flow was calculated and analyzed by the Gasturb Software.At the control schedule of the constant low spool corrected speed,the effect of the nozzle area variation on rotor speed difference between high and low pressure spool,surge margin,turbine inlet temperature,thrust and SFC were investigated for an aeroengine.The most reasonable core/bypass nozzle throat area was obtained by comparing these relations,thus the users were instructed how to utmost optimize the performance and extend operational life for engine.

关 键 词：大涵道比 分排涡扇发动机 喷管喉道面积 性能 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]