中国机械工程
中國機械工程
중국궤계공정
CHINA MECHANICAl ENGINEERING
2013年
21期
2867-2871
,共5页
赵运生%胡骏%屠宝锋%王志强
趙運生%鬍駿%屠寶鋒%王誌彊
조운생%호준%도보봉%왕지강
雷诺数%涡扇发动机%数值仿真%大涵道比%性能
雷諾數%渦扇髮動機%數值倣真%大涵道比%性能
뢰낙수%와선발동궤%수치방진%대함도비%성능
Reynolds number%turbofan%simulation%high bypass ratio%performance
为了评估雷诺数对某大涵道比涡扇发动机的影响，利用 Wassell 等修正方法，对发动机主要部件的特性进行了雷诺数修正，并利用发展的性能仿真程序进行计算和对比。结果表明，在高空低马赫数下，雷诺数对大涵道比涡扇发动机性能影响较大，造成发动机的推力减小约1.98%、耗油率增大约3.04%，同时影响发动机的喘振边界及共同工作线，降低其可用稳定裕度。
為瞭評估雷諾數對某大涵道比渦扇髮動機的影響，利用 Wassell 等脩正方法，對髮動機主要部件的特性進行瞭雷諾數脩正，併利用髮展的性能倣真程序進行計算和對比。結果錶明，在高空低馬赫數下，雷諾數對大涵道比渦扇髮動機性能影響較大，造成髮動機的推力減小約1.98%、耗油率增大約3.04%，同時影響髮動機的喘振邊界及共同工作線，降低其可用穩定裕度。
위료평고뢰낙수대모대함도비와선발동궤적영향，이용 Wassell 등수정방법，대발동궤주요부건적특성진행료뢰낙수수정，병이용발전적성능방진정서진행계산화대비。결과표명，재고공저마혁수하，뢰낙수대대함도비와선발동궤성능영향교대，조성발동궤적추력감소약1.98%、모유솔증대약3.04%，동시영향발동궤적천진변계급공동공작선，강저기가용은정유도。
For assessing the Reynolds number’s effect on a high bypass ratio turbofan,the correc-tion methods such as Wassell were used for the main component characteristics,and cooperated with a new performance program to simulate the effects of Reynolds number on engine’s performance.Re-sults show that Reynolds number has grievous effects on the turbofan in high flight and low Mach number region,the thrust is declined by near 1.98%,the specific fuel consumption is escalated by near 3.04%,the stall lines and operating lines are affected and the stall margin is declined as well.
