兼顾多状态的核心机驱动风扇级与高压压气机设计
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摘要
针对变循环发动机压缩系统多模式和多工况的工作特点,开展了核心机驱动风扇级(CDFS)多状态和多目标兼顾设计,CDFS、前涵道引射器和高压压气机气动一体化设计,大攻角范围、低损失可调导叶和静子设计。针对压缩系统的气动设计难点,在设计点选取、叶片造型、流场设计、调节规律设计方面提出了解决措施和优化方向。数值模拟与试验结果表明:实现了压缩系统在多模式下的性能兼顾,达到了预期的流量调节范围和涵道比调节范围,满足了设计指标要求。
According to the operating characteristics of multi-mode and multi-working conditions of the variable cycle engine compression system,the design of multi-state and multi-objective of CDFS,the design of the aerodynamic integration of the CDFS,forward vanable bypass ejector and high-pressure compressor,the design of the variable guide vanes and stators with range of the incidence angles and low loss were carried out. Aiming at the difficulties of aerodynamic design of the compression system,the solving measures and optimization direction were put forward in the aspects of design point selection,blade modeling,flow field design and regulation design. The results of numerical simulation and test show that the performance of compression system in multi-mode is realized,and the expected range of flow regulation and bypass ratio regulation is achieved,which can meet the requirements of design index.
According to the operating characteristics of multi-mode and multi-working conditions of the variable cycle engine compression system,the design of multi-state and multi-objective of CDFS,the design of the aerodynamic integration of the CDFS,forward vanable bypass ejector and high-pressure compressor,the design of the variable guide vanes and stators with range of the incidence angles and low loss were carried out. Aiming at the difficulties of aerodynamic design of the compression system,the solving measures and optimization direction were put forward in the aspects of design point selection,blade modeling,flow field design and regulation design. The results of numerical simulation and test show that the performance of compression system in multi-mode is realized,and the expected range of flow regulation and bypass ratio regulation is achieved,which can meet the requirements of design index.
引文
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[2]刘增文,王占学,黄红超,等.变循环发动机数值模拟[J].航空动力学报,2010,25(6):1310-1315.LIU Zengwen,WANG Zhanxue,HUANG Hongchao,et al. Numerical simulation on performance of variable cycle engines[J]. Journal of Aerospace Power,2010,25(6):1310-1315.(in Chinese)
[3]方昌德.变循环发动机[J].燃气涡轮试验与研究,2004,17(3):1-5.FANG Changde. Variable cycle engines[J]. Gas Turbine Experiment and Research,2004,17(3):1-5.(in Chinese)
[4] Gronstedt U T J,Pilidis P. Control optimization of the transient performance of the selective bleed variable cycle engine during mode transition[J].Journal of Engineering for Gas Turbines and Power,2002,124(1):75-81.
[5] Joseph Adams,Kenneth Hampsten,John Mayberry. Next generation Air Force spacelift[R].AIAA-2010-8723.
[6]刘大响.对加快发展我国航空动力的思考[J].航空动力学报,2001,16(1):1-7.LIU Daxiang. Deliberation upon advance of aeroengine development in China[J]. Journal of Aerospace Power,2001,16(1):1-7.(in Chinese)
[7]张鑫,刘宝杰.核心机驱动风扇级的气动设计特点分析[J].航空动力学报,2010,25(2):434-442.ZHANG Xin,LIU Baojie. Analysis of aerodynamic design characteristics of core driven fan stage[J]. Journal of Aerospace Power,2010,25(2):434-442.(in Chinese)
[8]张鑫,刘宝杰.核心机驱动风扇级的匹配特性分析[J].航空学报,2015,36(9):2850-2858.ZHANG Xin,LIU Baojie. Matching characteristics of core driven fan stage[J]. Acta Aeronautica Et Astronautica Sinica,2015,36(9):2850-2858.(in Chinese)
[9] Knott P R,Brausch J F,Bhutiani P K,et al. VCE early acoustic test results of General Electric's high-radius ratio coannular plug nozzle[R].NASA-CR-1980-99076.
[10] Vdoviak J W,Knott P R,Ebacker J A. Aerodynamic acoustic performance of YJ101 double bypass VCE with coannular plug nozzle[R].NASA-CR-1981-159869.
[11] French M W,Allen G L.NASA VCE test bed engine aerodynamic performance characteristics and test results[R]. AIAA-1981-1594.
[12] Rallabhandi S K,Mavris D N. Simultaneous airframe and propulsion cycle optimization for supersonic aircraft design[R].AIAA-2008-143.
[13]赖安卿,胡骏,屠宝锋.核心机驱动风扇级气动设计方案[J].航空动力学报,2014,29(9):2229-2238.LAI Anqing,HU Jun,TU Baofeng. Scheme on aerodynamic design of core driven fan stage[J]. Journal of Aerospace Power,2014,29(9):2229-2238.(in Chinese)
[14]黄磊,周拜豪,李清华,等.高切线速度低压比单级风扇设计技术及试验验证[J].燃气涡轮试验与研究,2016,29(6):16-20.HUANG Lei,ZHOU Baihao,LI Qinghua,et al. Design technology and experimental verification of a single stage fan with high tip speed and low pressure ratio[J]. Gas Turbine Experiment and Research,2016,29(6):16-20.(in Chinese)
[15]王前,胡骏,屠宝锋,等.核心机驱动风扇级可变弯度导叶设计方法[J].推进技术,2016,37(10):1859-1855.WANG Qian,HU Jun,TU Baofeng,et al. Method of variable camber inlet guide vanes design on core driven fan stage[J]. Journal of Propulsion Technology,2016,37(10):1859-1855.(in Chinese)
[16]苏桂英,孙立业.常规布局涡扇发动机实现变循环功能的技术途径探索[J].航空科学技术,2011(5):30-32.SU Guiying,SUN Liye. Analysis of the technical approach of actualizing VCE based on the conventional turbofan engine[J]. Aeronautical Science and Technology,2011(5):30-32.(in Chinese)
[17]张鑫.核心机驱动风扇级的气动设计及其与下游部件的匹配[D].北京:北京航空航天大学,2011.ZHANG Xin. Aerodynamic design of the CDFS and the matching of the CDFS with downstream componets[D]. Beijing:Beijing University of Aeronautics and Astronautics,2011.(in Chinese)