串联式TBCC后涵道引射器设计  

Design of rear bypass injector for tandem turbine based combined cycle engine

作　　者：谢健 李中龙 李丹 黄维娜 曾军 XIE Jian;LI Zhong-long;LI Dan;HUANG Wei-na;ZENG Jun(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2020年第1期12-18,53,共8页Gas Turbine Experiment and Research

摘　　要：对串联式TBCC发动机后涵道引射器开展了气动流道设计及模型试验研究,并通过数值计算与模型试验结果对比确定了后涵道引射器的性能特性。研究结果表明,背压降低,涵道比增大,总压恢复系数降低;内外涵总压比增大,涵道比和总压恢复系数呈降低趋势,总体匹配应避免内外涵压比过大;开度对涵道比有明显影响(开度越大,涵道比越大),但对总压恢复系数影响较小。后涵道引射器方案可以实现涵道比0.2以上、总压恢复系数不低于0.95,在满足此性能要求下调节机构应实现最大开度不小于10.0 mm。For the design of rear bypass injector of turbine based combined cycle(TBCC)engine,the re searches of aerodynamic flow path design and model test were carried out.Compared with the results of nu merical computation and model test,the performance characteristics of the bypass injector were obtained.The research results show that with the decrease of back pressure,bypass ratio will increase and total pres sure recovery coefficient will decrease.When total pressure ratio of internal and external bypass duct in creases,bypass ratio and total pressure recovery coefficient intend to decrease.Too large pressure ratio of internal and external bypass duct should be avoided.Open degree has obvious impact on bypass ratio,that bigger is the open degree,bigger is the bypass ratio.However,open degree has little impact on total pres sure recovery coefficient.With the bypass injector,bypass ratio above 0.2 and total pressure recovery coeffi cient not less than 0.95 could be achieved.For meeting this performance,the maximum open degree should not less than 10.0 mm for bypass injector adjusting mechanism.

关 键 词：航空发动机 串联式TBCC 后涵道引射器 涵道比 内外涵总压比 开度 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程] V231.3