两种动态压力测量装置试验对比研究
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摘要
针对齐平安装与准无限长管两种动态压力测量装置的结构特征,设计了多种动态压力探针。采用正弦压力发生器进行动态压力特性标定,量化了工程应用中两种结构的不同感压管腔对动态压力测量误差的影响,并在发动机总压畸变试验中进行了对比研究。结果表明,齐平安装结构中,传感器安装引起的小容腔对动态压力测量误差影响不大;准无限长管结构中,感压管腔的存在会导致动态压力幅频特性波动、相位滞后,且波动量与感压管腔长度正相关,相位滞后与感压管腔大小呈线性特征。
Aiming at the structure characteristics of two measuring devices of dynamic pressure(flush-mounted and quasi-infinite tube), multiple dynamic pressure probes were designed and dynamic characteristics were calibrated using sine pressure generator. Measurement errors on dynamic pressure due to different cavity characteristics of two devices were quantified and experimental comparison research on pressure distortion test of aero-engine was carried out. The results indicate that the impact on measuring dynamic pressure of flush-mounted structure was small. The cavity of quasi-infinite line structure results in fluctuating of amplitude-frequency characteristic and lag of phase. It is positive correlation between fluctuating size and length of cavity. It has good linear feature between lag of phase and cavity size.
Aiming at the structure characteristics of two measuring devices of dynamic pressure(flush-mounted and quasi-infinite tube), multiple dynamic pressure probes were designed and dynamic characteristics were calibrated using sine pressure generator. Measurement errors on dynamic pressure due to different cavity characteristics of two devices were quantified and experimental comparison research on pressure distortion test of aero-engine was carried out. The results indicate that the impact on measuring dynamic pressure of flush-mounted structure was small. The cavity of quasi-infinite line structure results in fluctuating of amplitude-frequency characteristic and lag of phase. It is positive correlation between fluctuating size and length of cavity. It has good linear feature between lag of phase and cavity size.
引文
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[16]刘大响,叶培梁,胡骏,等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:国防工业出版社,2004.
[2]Lenherr C L,Kalfas A I,Abhari R S.High temperature fast response aerodynamic probe[R].ASME GT2010-23010,2010.
[3]Englund D R,Richards W Bruce.The infinite line pressure probe[R].NASA TM-83582,1984.
[4]Van de Wyer N,Brouckaert J F,Miorini R.On the determination of the transfer function of infinite line pressure probes for turbo machinery applications[R].ASME GT2012-69563,2012.
[5]Wegner M A,Nance D,Ahuja K K.Characterization ofshort and infinite-line pressure for in-duct acoustic measurements under hostile environment[R].AIAA2007-3443,2007.
[6]Nyland T W,Englund D R,Anderson R C.On the dynamics of short pressure probes:some design factors affecting frequency response[R].NASA TND-6151,1971.
[7]郭勇,王效葵,王洪伟.高频压力探针动态性能的补偿方法[J].航空动力学报,2005,20(2):273-277.
[8]李继超,王偲臣,林峰,等.一种容腔效应标定技术及其在高频响动态探针中的应用[J].航空动力学报,2011,26(12):2749-2756.
[9]杨林,王偲臣,林峰,等.基于半无限引压管效应的动态压力测量方法[J].航空动力学报,2014,29(10):2457-2463.
[10]Bergh H,Tijdeman H.Theoretical and experimental results for the dynamic response of pressure measuring sys-tems[R].NLR-TR-F.238,1965.
[11]王维赉.动态压力测量原理及方法[M].北京:中国计量出版社,1986.
[12]Ferrara G,Ferrari L,Sonni G.Experimental characterization of a remoting system for dynamic pressure sensors[R].ASME GT2005-68733,2005.
[13]罗华锋.航空发动机低频小幅值气体脉动压力校准系统研究[D].成都:电子科技大学,2009.
[14]樊嘉峰,吴晨,韩伟.一种小型管腔动态压力测试系统:中国,ZL201120576781.0[P].2012-09-05.
[15]王维,唐磊,王棋.压力测试管道管腔效应研究[J].计测技术,2012,32(SO):81-86.
[16]刘大响,叶培梁,胡骏,等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:国防工业出版社,2004.