几何可调喷管的结构特点及发展
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摘要
可调喷管是影响军用发动机推力性能和飞行器总体性能的关键部件。以介绍航空燃气涡轮发动机为主兼顾火箭发动机以及组合循环发动机,对几何可调喷管的结构特点、工作原理以及发展状况进行了归纳总结,指出几何可调喷管结构设计的关键技术。
Variable nozzle is the key component that affects the thrust performance of military propulsion system and the overall performance of aircraft. Focused on the aviation gas turbine engine,both the rocket propulsion and the combined cycle engine were taken into account. The structure characteristics,working principle and the development of variable nozzles were summarized and concluded. The critical technologies for variable nozzles structure design were proposed.
Variable nozzle is the key component that affects the thrust performance of military propulsion system and the overall performance of aircraft. Focused on the aviation gas turbine engine,both the rocket propulsion and the combined cycle engine were taken into account. The structure characteristics,working principle and the development of variable nozzles were summarized and concluded. The critical technologies for variable nozzles structure design were proposed.
引文
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[17]MACE J,SMERECZNIAK P,KREKELER G.Advanced thrust vectoring nozzles for supercruise fighter aircraft[J].Al AA 89-2816,1989.
[18]李晓明,伏宇.轴对称矢量喷管机构优化设计[J].燃气涡轮试验与研究,2006,19(3):1-5.
[19]KAUSER F B.An overview of gas turbine propulsion technology[J].AIAA 94-2828,1994.
[20]RUSBARSKY G.F-15 STOL and maneuver technology demonstrator flight test progress report[J].AIAA 90-1269,1990.
[21]CLOUHG B.Short take-off and landing maneuver technology demonstrator(S/MTD)lessons learned:integrated light propulsion control[J].AIAA 90-3307,1990.
[22]DANIEL L C,MARY L M.Experimental investigation of spherical-convergent-flap thrust-vectoring two-dimensional plug nozzles[J].Al AA 93-2431,1993.
[23]HAWKES T M.IHPTET exhaust nozzle technology demonstrator[J].AIAA 93-2569,1993.
[24]龚正真.航空发动机推力矢量喷管研究[C].中国航空学会21世纪航空动力发展研讨会论文集.北京:中国航空学会,2000:251-257.
[25]G.P.萨顿,O.比布拉兹.火箭发动机基础[M].洪鑫,张宝炯,译.北京:科学出版社,2003.
[26]KAZUHIDE M,HIROYUKI K,HIROMU S.Conception design of flight demonstrator vehicles for the ATREX engine[J].AIAA 2003-7028,2003.
[27]TAGUCHI H,FUTAMURA H,SHIMODAIRA K.Design study on hypersonic engine components for TBCC space planes[J].AIAA 2003-7006,2003.
[28]LEDERER R.Testing the actively cooled,fully variable hypersonic demonstrator nozzle[J].AIAA 96-4550,1996.
[29]SUETIN A G,KARTSW B V.Fundmentals of appearance formation and design solutions for supersonic ramjet[J].AIAA 93-2483,1993.
[30]庞越华,班大伟.耦合场下固体火箭发动机喷管的动力学分析[J].机械工程师,2013(10):77-80.
[31]刘斌.一种新型可调喉径喷管的结构设计与分析[J].固体火箭技术,2012,35(1):53-56.
[2]LOPEZ-DFEZ A,RODRFGUEZ M,SAN SEGUNDO M P.Applications of variable area nozzles for civil airplane[J].AIAA 98-3102,1998.
[3]FAZAL B K.An overview of gas Turbine propulsion technology[J].AIAA 94-2828,1994.
[4]周建军,尹自宾.固体火箭发动机单向可调喷管转换控制研究[J].航空兵器,2012(5):43-47.
[5]HARRY W B.The variable nozzle as a means of maintaining rocket engine efficiency when throttling[J].AIAA 64-4117,1964.
[6]SUETIN A G,MTSEV B V.Fundamentals of appearance formation and design solutions for supersonic ramjet[J].AIAA 1993-2483,1993.
[7]邵明玉,王志刚,陈凤明.复合调节固冲发动机性能分析[J].固体火箭技术,2015,38(4):481-486.
[8]梁俊龙,吴宝元,李斌.几何结构可调的亚燃冲压发动机性能研究[J].火箭推进,2010,36(2):1-4.
[9]黄河峡,谭慧俊,周唯阳,等.一种带中心体的TBCC可调喷管的设计与仿真[J].南京航空航天大学学报,2013,45(5):658-664.
[10]KUCHAR A P.Variable convergent-divergent exhaust nozzle aerodynamics[J].AIAA 1989 299-336,1989.
[11]ALFORD J S,TAYLOR R P.Aerodynamic stability considerations of high-pressure ratio,variable-geometry jet nozzles[J].AIAA 64-247,1964.
[12]CAPONE F,SMERECZNIAK P,SPETNAGEL D.Comparative investigation of multiplane thrust vectoring nozzles[J].AIAA 92-3263,1992.
[13]JOHN S O,ROSS H,MICHAEL D.Ferguson.Initial flight test evaluation of the F-15 ACTIVE axisymmetric vectoring nozzle performance[J].AIAA 1998-3871,1998.
[14]DOANE P,BURSEY R,SCHKOLNIC G.F-15 ACTIVE:a flexible propulsion integration test bed[R].AIAA 94-3360,1994.
[15]MISHLER R,WILKINSON T.Emerging airframe/propulsion integration technologies at general electric[J].AIAA92-3335,1992.
[16]JIMENEZ A.Thrust vectoring for advance fighter aircraft,propulsion package development[J].AIAA 2001-3991.2001.
[17]MACE J,SMERECZNIAK P,KREKELER G.Advanced thrust vectoring nozzles for supercruise fighter aircraft[J].Al AA 89-2816,1989.
[18]李晓明,伏宇.轴对称矢量喷管机构优化设计[J].燃气涡轮试验与研究,2006,19(3):1-5.
[19]KAUSER F B.An overview of gas turbine propulsion technology[J].AIAA 94-2828,1994.
[20]RUSBARSKY G.F-15 STOL and maneuver technology demonstrator flight test progress report[J].AIAA 90-1269,1990.
[21]CLOUHG B.Short take-off and landing maneuver technology demonstrator(S/MTD)lessons learned:integrated light propulsion control[J].AIAA 90-3307,1990.
[22]DANIEL L C,MARY L M.Experimental investigation of spherical-convergent-flap thrust-vectoring two-dimensional plug nozzles[J].Al AA 93-2431,1993.
[23]HAWKES T M.IHPTET exhaust nozzle technology demonstrator[J].AIAA 93-2569,1993.
[24]龚正真.航空发动机推力矢量喷管研究[C].中国航空学会21世纪航空动力发展研讨会论文集.北京:中国航空学会,2000:251-257.
[25]G.P.萨顿,O.比布拉兹.火箭发动机基础[M].洪鑫,张宝炯,译.北京:科学出版社,2003.
[26]KAZUHIDE M,HIROYUKI K,HIROMU S.Conception design of flight demonstrator vehicles for the ATREX engine[J].AIAA 2003-7028,2003.
[27]TAGUCHI H,FUTAMURA H,SHIMODAIRA K.Design study on hypersonic engine components for TBCC space planes[J].AIAA 2003-7006,2003.
[28]LEDERER R.Testing the actively cooled,fully variable hypersonic demonstrator nozzle[J].AIAA 96-4550,1996.
[29]SUETIN A G,KARTSW B V.Fundmentals of appearance formation and design solutions for supersonic ramjet[J].AIAA 93-2483,1993.
[30]庞越华,班大伟.耦合场下固体火箭发动机喷管的动力学分析[J].机械工程师,2013(10):77-80.
[31]刘斌.一种新型可调喉径喷管的结构设计与分析[J].固体火箭技术,2012,35(1):53-56.