航空科学技术
航空科學技術
항공과학기술
AERONAUTICAL SCIENCE AND TECHNOLOGY
2014年
8期
54-59
,共6页
大涵道比%涡扇发动机%涡轮导向器%喷口%台架性能
大涵道比%渦扇髮動機%渦輪導嚮器%噴口%檯架性能
대함도비%와선발동궤%와륜도향기%분구%태가성능
high bypass ratio%turbofan engine%turbine stator%nozzle throat%bench performance
理论分析大涵道比涡扇发动机高/低压涡轮导向器、内/外涵喷口面积变化对发动机整机性能及各部件的影响。采用大涵道比涡扇发动机总体稳态计算程序，在控制低压转子转速不变的条件下，计算上述部件单一几何面积变化对发动机推力、耗油率、转差、裕度、排气温度等总体性能参数的影响，及放大面积后风扇、增压级和高压压气机等压缩部件工作点及喘振裕度的变化趋势，为大涵道比涡扇发动机整机性能调试提供指导。
理論分析大涵道比渦扇髮動機高/低壓渦輪導嚮器、內/外涵噴口麵積變化對髮動機整機性能及各部件的影響。採用大涵道比渦扇髮動機總體穩態計算程序，在控製低壓轉子轉速不變的條件下，計算上述部件單一幾何麵積變化對髮動機推力、耗油率、轉差、裕度、排氣溫度等總體性能參數的影響，及放大麵積後風扇、增壓級和高壓壓氣機等壓縮部件工作點及喘振裕度的變化趨勢，為大涵道比渦扇髮動機整機性能調試提供指導。
이론분석대함도비와선발동궤고/저압와륜도향기、내/외함분구면적변화대발동궤정궤성능급각부건적영향。채용대함도비와선발동궤총체은태계산정서，재공제저압전자전속불변적조건하，계산상술부건단일궤하면적변화대발동궤추력、모유솔、전차、유도、배기온도등총체성능삼수적영향，급방대면적후풍선、증압급화고압압기궤등압축부건공작점급천진유도적변화추세，위대함도비와선발동궤정궤성능조시제공지도。
Components area variation effect, including HPT, LPT, Fan nozzle and core nozzle, on performance of High Bypass Ratio (HBPR) Turbofan Engine and its components were analyzed theoretically. To ifnd out each component’s geometry area variation effect on engine performance parameters such as thrust, SFC, difference of HP-LP rotation speed, surge margin, exhaust temperature etc., the HBPR Turbofan Engine steady state simulation model was employed, with the constant corrected LP rotation speed setting. Along with the area enlargement, the Fan, Booster and HPC cooperating point and surge margin was changed. Studies about these changing trends were also involved. This work is a way to grantee engine performance test.
