分开排气涡扇发动机的热力循环分析  

Analysis of thermodynamic cycle for separated flow turbofan engine

作　　者：杨锟[1,2] 屠秋野 施洋[1,2] 蔡元虎 蒋平[3] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]先进航空发动机协同创新中心,北京100191 [3]中国航空发动机集团有限公司商用航空发动机有限责任公司,上海200241

出　　处：《航空动力学报》2017年第9期2187-2192,共6页Journal of Aerospace Power

摘　　要：基于燃气发生器的概念分析了分开排气涡扇发动机的效率划分。在此基础上,通过理论推导证明了分开排气涡扇发动机的最佳外涵风扇增压比的存在判据,及其单位推力、效率和耗油率极值的等价性。给出的判据可以作为实际分排涡扇发动机设计中的最佳外涵风扇增压比的选择依据。针对两型大涵道比分开排气涡扇发动机热力循环分析的结果表明:当外内涵排气速度的比值与风扇、低压涡轮效率的乘积相等时,发动机的总效率和单位推力最大,耗油率最低,从而证明了本文给出的效率划分和最佳外涵风扇增压比判据是合理的。The efficiency of separated flow turbofan engine was analyzed based on the definition of gas generator. It proved the existence criterion of the optimum fan pressure rati- o and the equivalence of extreme value of the specific thrust, the total efficiency and the spe- cific fuel consumption by theoretical deduction on the basis of the efficiency definitions. This criterion could be used to determine the optimum fan pressure ratio for separated flow turbo- fan engine in practical design progress. The parametric study results of two different high- bypass-ratio separated flow turbofan engines demonstrated that when the ratio of bypass and primary exhaust velocity equaled to the product of fan and low pressure turbine efficiencies, the overall efficiency and specific thrust reached their maximums and specific fuel consump- tion reached its minimum, proving the validity of the criterion.

关 键 词：大涵道比分开排气涡扇发动机 燃气发生器 效率 最佳外涵风扇增压比 耗油率 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]