提高进气道冲压阻力测量精度的方法
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摘要
为提高发动机飞行推力测量精度,对进气道冲压阻力测量计算方法进行了研究。鉴于进气道测量耙总压静压测点不遵循等环面分布,采用数值插值法获得等环面中心点的总压静压值,计算表明:靠近壁面的实际测点与其对应的等环面中心点之间的总压静压差异明显,总压最大差值为1. 0 kPa,静压最大差值为0. 73 kPa。分析了附面层厚度、分区域计算累加法、全区域计算平均法对流量、流速、冲压阻力的影响,结果表明:附面层造成的空气流量最大误差值可达1. 94 kg/s,差异较明显;采用分区域计算累加法与采用全区域总压静压平均值计算的空气流量差异小。采用分区域计算累加法与采用全区域总压静压平均值计算的冲压阻力最大差值仅为0. 09 kN,差异很小,两种方法在推力直接确定中都具有应用价值。
In order to improve the accuracy of engine flight thrust measurement,the measurement and calculation method of inlet stamping resistance were studied. In view of the fact that the total pressure and static pressure measuring points do not follow the equel torus area distribution on the inlet measurement rake,the value of the total pressure and static pressure at the center point of the equel torus area were obtained by numerical interpolation method. Calculation results show that the total pressure and static pressure difference between the actual measuring points near the wall surface and the corresponding central points of the equel torus area are obvious,the maximum difference of total pressure is 1. 0 kPa,and the maximum difference of static pressure is 0. 73 kPa. The influences of the boundary layer thickness,subregional computation accumulation method and whole area calculation average method on the flow,flow velocity and stamping resistance were analyzed. The results show that. the maximum error value of air flow caused by boundary layer can reach 1. 94 kg/s,with obvious difference. The difference is small between the air flow calculated by the subregional computation accumulation method and that calculated by the average value of pressure in the whole area. The maximum difference between the stamping resistance calculated by subregional computation accumulation method and that calculated by the average value of pressure in the whole area is only 0. 09 kN,and the difference is very small,both methods are valuable in direct thrust determination.
In order to improve the accuracy of engine flight thrust measurement,the measurement and calculation method of inlet stamping resistance were studied. In view of the fact that the total pressure and static pressure measuring points do not follow the equel torus area distribution on the inlet measurement rake,the value of the total pressure and static pressure at the center point of the equel torus area were obtained by numerical interpolation method. Calculation results show that the total pressure and static pressure difference between the actual measuring points near the wall surface and the corresponding central points of the equel torus area are obvious,the maximum difference of total pressure is 1. 0 kPa,and the maximum difference of static pressure is 0. 73 kPa. The influences of the boundary layer thickness,subregional computation accumulation method and whole area calculation average method on the flow,flow velocity and stamping resistance were analyzed. The results show that. the maximum error value of air flow caused by boundary layer can reach 1. 94 kg/s,with obvious difference. The difference is small between the air flow calculated by the subregional computation accumulation method and that calculated by the average value of pressure in the whole area. The maximum difference between the stamping resistance calculated by subregional computation accumulation method and that calculated by the average value of pressure in the whole area is only 0. 09 kN,and the difference is very small,both methods are valuable in direct thrust determination.
引文
1雷晓波,张强,文敏,等.航空发动机安装节推力测量技术与试验研究[J].航空学报,2017,38(12):1-8Lei Xiaobo,Zhang Qiang,Wen Min,et al.Mount thrust measurement technique for aero-engines and its tests[J].Acta Aeronautica et Astronautica Sinica,2017,38(12):1-8
2廉筱纯,吴虎.航空发动机原理[M].北京:国防工业出版社,2005:14-16Lian Xiaochun,Wu Hu.Principles of aeroengine[M].Beijing:National Defense Industry Press,2005:14-16
3 Burcham S,Frank W.An investigation of two variations of the gas generator method to calculate the thrust of the afterburning turbo fan engines installed in an F-111A airplane:NASA-TND-6297NASA[R].Washington:1971
4 Ray R J.Evaluating the dynamic response of in-flight thrust calculation techniques during throttle transients:NASA-TM-4591[R].Edwards:NASA,1994
5 Thomas B.The F/A-18 high-AOA research vehicle with thrust-vectoring control system:NASA-TM-5097[R].Washington:NASA,1996
6 Paul W C.A comprehensive approach to in-flight thrust determination:NASA-TM-79-3[R].Washington:NASA,1994
7 Timothy R,Robert L.Full flight envelope direct thrust measurement on a supersonic aircraft:NASA-TM/206560[R].Washington:NASA,1998
8 John S.Initial flight test evaluation of the F-15 ACTIVE axisymmetric vectoring nozzle performance:NASA-TM/120904[R].Washington:NASA,1998
9 John S,Robert L.Selected performance measurement of the F-15ACTIVE axisymmetric thrust-vectoring nozzle:NASA-TM/348096[R].Washington:NASA,1999
10雷晓波,李密,张强,等.航空发动机推力直接测量飞行试验[J].航空动力学报,2018,33(7):1631-1638Lei Xiaobo,Li Mi,Zhang Qiang,et al.Direct thrust measurement flight test of aero-engine[J].Journal of Aerospace Power,2018,33(7):1631-1638
11杜鹤龄.航空发动机推力的测量和确定方法[J].航空动力学报,1997,12(4):389-392Du Heling.Measurement and determination of aeroengine thrust[J].Journal of Aerospace Power,1997,12(4):389-392
12赵海刚,申世才,张晓飞,等.涡扇发动机空气流量测量飞行试验[J].航空动力学报,2012,27(8):1778-1883Zhao Haigang,Shen Shicai,Zhang Xiaofei,et al.Flight test of mass flow measurement of turbofan engine[J].Journal of Aerospace Power,2012,27(8):1778-1883
13 Bui T,Oates D L.Design and evaluation of a new boundary-layer measurement rake for flight testing:NASA-TM-2000-209014[R].Washington:NASA,2000
14雷晓波,雷蒂远,郝晓乐,等.飞行载荷模式识别方法的研究及应用[J].应用力学学报,2018,35(2):241-247Lei Xiaobo,Lei Diyuan,Hao Xiaole,et al.Study and application of flight load pattern recognition methods[J].Journal of Applied Mechanics,2018,35(2):241-247
2廉筱纯,吴虎.航空发动机原理[M].北京:国防工业出版社,2005:14-16Lian Xiaochun,Wu Hu.Principles of aeroengine[M].Beijing:National Defense Industry Press,2005:14-16
3 Burcham S,Frank W.An investigation of two variations of the gas generator method to calculate the thrust of the afterburning turbo fan engines installed in an F-111A airplane:NASA-TND-6297NASA[R].Washington:1971
4 Ray R J.Evaluating the dynamic response of in-flight thrust calculation techniques during throttle transients:NASA-TM-4591[R].Edwards:NASA,1994
5 Thomas B.The F/A-18 high-AOA research vehicle with thrust-vectoring control system:NASA-TM-5097[R].Washington:NASA,1996
6 Paul W C.A comprehensive approach to in-flight thrust determination:NASA-TM-79-3[R].Washington:NASA,1994
7 Timothy R,Robert L.Full flight envelope direct thrust measurement on a supersonic aircraft:NASA-TM/206560[R].Washington:NASA,1998
8 John S.Initial flight test evaluation of the F-15 ACTIVE axisymmetric vectoring nozzle performance:NASA-TM/120904[R].Washington:NASA,1998
9 John S,Robert L.Selected performance measurement of the F-15ACTIVE axisymmetric thrust-vectoring nozzle:NASA-TM/348096[R].Washington:NASA,1999
10雷晓波,李密,张强,等.航空发动机推力直接测量飞行试验[J].航空动力学报,2018,33(7):1631-1638Lei Xiaobo,Li Mi,Zhang Qiang,et al.Direct thrust measurement flight test of aero-engine[J].Journal of Aerospace Power,2018,33(7):1631-1638
11杜鹤龄.航空发动机推力的测量和确定方法[J].航空动力学报,1997,12(4):389-392Du Heling.Measurement and determination of aeroengine thrust[J].Journal of Aerospace Power,1997,12(4):389-392
12赵海刚,申世才,张晓飞,等.涡扇发动机空气流量测量飞行试验[J].航空动力学报,2012,27(8):1778-1883Zhao Haigang,Shen Shicai,Zhang Xiaofei,et al.Flight test of mass flow measurement of turbofan engine[J].Journal of Aerospace Power,2012,27(8):1778-1883
13 Bui T,Oates D L.Design and evaluation of a new boundary-layer measurement rake for flight testing:NASA-TM-2000-209014[R].Washington:NASA,2000
14雷晓波,雷蒂远,郝晓乐,等.飞行载荷模式识别方法的研究及应用[J].应用力学学报,2018,35(2):241-247Lei Xiaobo,Lei Diyuan,Hao Xiaole,et al.Study and application of flight load pattern recognition methods[J].Journal of Applied Mechanics,2018,35(2):241-247