基于多设计点方法的陶瓷基材料涡桨发动机热力循环分析

Thermal Cycle Analysis of Turboprop with Ceramic Matrix Composite Based on Multiple Design Points Approach

关键词:  陶瓷基复合材料  涡桨发动机  多设计点方法  耗油率  单位推力

Key words:  Ceramic matrix composite  Turboprop  Multiple design points approach  Specific fuel consumption  Specific power

摘要:

为了研究陶瓷基复合材料（CMC）对先进民用涡桨发动机总体性能带来的提升，建立了双转子燃气发生器自由涡轮式涡桨发动机多设计点热力循环分析模型，并编制了相应的程序。计算分析了采用常规金属材料、仅高压涡轮导向器采用CMC以及整个高压涡轮部件采用CMC的涡桨发动机总体性能。结果表明：（1）高压涡轮导向器采用CMC且保持高压涡轮转子进口温度与金属材料一致，耗油率和单位功率性能最多分别提升1%和1.1%，同时可以使燃烧室出口温度最多降低83℃。（2）高压涡轮导向器采用CMC且保持燃烧室出口温度一致，耗油率和单位功率性能最多提升1.6%和6.5%。（3）当整个高压涡轮采用CMC时，耗油率和单位功率性能最多提升7.8%和20%。

Abstract:

For studying the benefits for overall performance of the advanced civil turboprop by using ceramic matrix composite （CMC）， a multiple design points approach and the corresponding code were developed to investigate the cycle of a turboprop with twin shafts gas generator and a free power turbine. Performance of a turboprop using either metallic or CMC in the high pressure turbine （HPT） vanes or CMC in the whole HPT was examined. The analysis demonstrates that： （1） Using CMC in the HPT vanes at the same HPT rotor inlet temperature can improve specific fuel consumption and specific power by 1% and 1.1%， respectively， while decrease the burner outlet temperature by 83℃ at the same time. （2） The maximum improvement in specific fuel consumption and specific power is 1.6%and 6.5%， respectively ， while using CMC in the HPT vanes at the same burner outlet temperature. （3） While using CMC in the whole HPT， the maximum improvement in specific fuel consumption and specific power is 7.8% and 20%， respectively.