内燃波转子技术对燃气涡轮发动机性能影响  

Effect of internal combustion wave rotor technology on performance of gas turbine engine

作　　者：李建中[1,2] 巩二磊[1] 温泉[2] 王家骅[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司航空动力机械研究所,湖南株洲421002

出　　处：《航空动力学报》2012年第9期1928-1934,共7页Journal of Aerospace Power

基　　金：高等学校博士学科点专项科研基金(20093218120013);中央高校基本科研业务费专项资金(No.NS2012017)

摘　　要：为研究内燃波转子技术提高燃气涡轮发动机性能变化规律,建立内燃波转子燃气涡轮发动机热力循环分析模型,开展内燃波转子通道出口气流马赫数、压气机压比等参数变化对燃气涡轮发动机性能的影响研究,探讨了内燃波转子燃气涡轮发动机热力循环状态参数变化规律.研究结果表明:当压气机压比等于3.6时,发动机比推力和热循环总效率最大提高23.709%,耗油率最大减少19.165%;当通道出口气流马赫数等于0.6时,发动机比推力最大增幅达23.736%,此时压气机压比为4.4、发动机热循环总效率32.216%和耗油率减少24.366%,熵增减少7.864%,验证了内燃波转子技术能够提高燃气涡轮发动机总体性能.研究结果为深入开展内燃波转子燃气涡轮发动机基础理论和关键技术研究奠定基础.To investigate internal combustion wave rotor technology which improved performance of gas turbine engine,the thermodynamic cycle analysis model of an internal combustion wave rotor gas turbine engine was established.When the parameters of exit Mach number of the internal combustion wave rotor channel and compressor pressure ratio were changed,their influence on the performance of the internal combustion wave rotor gas turbine engine was investigated,and the variable disciplinarian of thermodynamic cycle parameter of the internal combustion wave rotor was discussed.When the compressor pressure ratio equals 3.6,the specific cycle thrust and thermal efficiency increases by up to 23.709%,and the specific fuel consumption decreases by up to 19.165%.When the exit Mach number of the internal combustion wave rotor channel equals 0.6,the specific cycle thrust and thermal efficiency increase by up to 23.736%,the corresponding compressor pressure ratio equals 4.4 at the same time,the thermal efficiency improves 32.216%,specific fuel consumption decreases by 24.366% and entropy generation decreases by 7.864%.It is validated that the technology of the internal combustion wave rotor can enhance the performance of gas turbine engine.The results can provide theory and practice for lucubrating the key technology of the internal combustion wave rotor gas turbine engine.

关 键 词：燃气涡轮发动机 内燃波转子 热力循环 燃气涡轮发动机性能 出口气流马赫数 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]