梁春华,杨东丹,刘红霞,尚守堂.航空发动机新型补燃增推燃烧室的现状与发展[J].航空发动机,2012,38(5):1-6
航空发动机新型补燃增推燃烧室的现状与发展
Present and Future Development of Advanced Second Burner forAeroengine
  
DOI:
中文关键词:  补燃增推燃烧室  涡轮后框架燃烧室  涡轮间燃烧室  性能  航空发动机
英文关键词:second burner  integrated turbine rear frame afterburner,Inter-stage Turbine Burner  perform ance  aeroengine
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作者单位
梁春华,杨东丹,刘红霞,尚守堂 中航工业沈阳发动机设计研究所沈阳1 10015 
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中文摘要:
      涡轮后框架一体化加力燃烧室(简称涡轮后框架燃烧室)和涡轮间燃烧室均是为了提高推进效率和降低耗油率而新近开发和验证的2种先进补燃增推燃烧室。综述了2种燃烧室的基本结构、研制背景、发展历程和目前研究进展,总结了从众多研究中获得的这2种燃烧室相对常规结构的性能特点,如涡轮后框架燃烧室结构紧凑,流体损失小,结构耐久性好;涡轮间燃烧室推进效率高,热效率高。还指示了这2种燃烧室的发展趋势。
英文摘要:
      Integrated turbine rear frame afterburner and Inter—stage Turbine Burner (ITB)are advanced augmented burners reeendy developed and demonstrated in order to improve propulsive efi ciency and reduce specific fuel consumption.Their basic structures,development background and progress and current state burners were overviewed.The results obtained from the issued documents show that the performance characteristics with compact structure,low flow loss and high endurance are demonstrated for integrated turbine rear frame afterburner and the performance characteristics with high thrust and thermal eficiency are demonstrated for ITB.Their future trend are forecasted.
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