Investigation of performance approximate revision methods for engine with adjustable convergence nozzle in ram pressure calibration of altitude simulated test
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摘要:
针对控制规律与海拔高度相关带可调收敛喷管发动机,提出了在冲压条件下进行校准试验的方法。该方法通过冲压与等冲压试验结果比较获得修正系数,实现冲压条件下校准试验结果的近似修正。针对某型涡扇发动机,进行了高空台试验和总体性能仿真,获得了喷管控制偏差时发动机性能变化比例,基于冲压条件下试验结果修正得到了标准海平面条件下发动机性能。该方法表明:冲压条件下进行校准试验的方法是可行的,获取的发动机推力等主要性能参数与出厂试车结果相差小于2.0%。
Abstract:A method of revising the performance of an engine with adjustable convergent nozzle caused by nozzle control deviation in ram pressure calibration of Altitude Simulated Test was presented. According to this method, the correction coefficient was obtained by comparing the test results under ram pressure condition with those under equal ram pressure condition. The approximate correction of calibration test results under the condition of ram pressure was realized. For a turbofan engine, the experiments in altitude test and the overall performance simulation were carried out. The variation of engine performance under nozzle control deviation was obtained, and the correction of calibration test results under ram pressure condition was realized. The results showed that this calibration test method was feasible under the condition of ram pressure, and the difference between the engine thrust and other main performance parameters obtained by the above method and the factory test results was less than 2.0%.
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$ {W_{\text{a}}} $ 空气质量流量(kg/s) Ma 马赫数 $ {W_{\text{f}}} $ 燃油质量流量(kg/h) $ {F_{\text{g}}} $ 总推力(N) A 面积(m2) $ {F_{\text{m}}} $ 测量推力(N) p 气体压力(Pa) V 气流速度(m/s) T 气体温度(K) 下标 R 气体常数(J/(kg·K)) t 滞止的,总的 $ \lambda $ 速度系数 c 规定的飞行状态下 $ q (\lambda ) $ 流量函数 r 环面的 H 飞行高度(km) sch 高空舱内的 表 1 发动机主要性能参数差异(nlc=103.86%)
Table 1. Main parameters deviation for engine performance (nlc=103.86%)
参数 相对变化量/% $ {n_{{\text{lc}}}} $ $ {n_{{\text{hc}}}} $ −0.07 $ {W_{{\text{ac}}}} $ −0.19 $ {W_{{\text{fc}}}} $ −2.81 $ {T_{{\text{5c}}}} $ −1.32 $ {F_{{\text{gc}}}} $ −2.26 $ {\pi _{\text{f}}} $ −1.61 表 2 A8面积变化发动机仿真计算结果
Table 2. Simulate results for engine caused by A8 deviation
参数 相对变化量/% $ {A_8} $ 2.01 $ {\pi _{\text{f}}} $ −1.45 $ {n_{\text{h}}} $ −0.37 $ {T_{\text{5}}} $ −1.05 $ {W_{\text{f}}} $ −2.78 $ {F_{\text{g}}} $ −2.09 表 3 修正后的校准试验结果与出厂数据比较
Table 3. Revised calibration test results vs. producer data
参数 相对变化量/% $ {n_{{\text{lc}}}} $ $ {n_{{\text{hc}}}} $ −0.15 $ {W_{{\text{fc}}}} $ 1.90 $ {T_{{\text{5c}}}} $ 0.78 $ {F_{{\text{gc}}}} $ −0.53 -
[1] SEBOURN C. Calculation of the discharge coefficient of close-coupled bellmouth flowmeters installed in propulsion test facilities: AIAA 2004-2732 [R]. Reston,US: AIAA,2004. [2] 刘志友,郭荣伟,侯敏杰,等. 航空发动机在高空台上的H0/Ma0试验分析[J]. 航空动力学报,2007,22(7): 1173-1178. LIU Zhiyou,GUO Rongwei,HOU Minjie,et al. Analysis of H=0 & Ma=0 test for aero-engine at ATF[J]. Journal of Aerospace Power,2007,22(7): 1173-1178. (in ChineseLIU Zhiyou, GUO Rongwei, HOU Minjie, et al. Analysis of H=0 & Ma=0 test for aero-engine at ATF[J]. Journal of Aerospace Power, 2007, 22(7): 1173-1178. (in Chinese) [3] 魏海涛,赵博,杨晓. 涡喷涡扇发动机试车台校准[J]. 计量技术,2002(2): 25-27. WEI Haitao,ZHAO Bo,YANG Xiao. Calibration of turbojet turbofan engine test bench[J]. Measurement Technique,2002(2): 25-27. (in ChineseWEI Haitao, ZHAO Bo, YANG Xiao. Calibration of turbojet turbofan engine test bench[J]. Measurement Technique, 2002(2): 25-27. (in Chinese) [4] 王辰辰,李新良,李程,等. 航空矢量发动机试车台推力校准技术综述[J]. 计测技术,2015,35(4): 10-14. WANG Chenchen,LI Xinliang,LI Cheng,et al. Thrust calibration technology of areo vector engine test cell[J]. Metrology and Measurement Technology,2015,35(4): 10-14. (in ChineseWANG Chenchen, LI Xinliang, LI Cheng, et al. Thrust calibration technology of areo vector engine test cell[J]. Metrology and Measurement Technology, 2015, 35(4): 10-14. (in Chinese) [5] 赵涌,侯敏杰,陈冕,等. 航空发动机高空模拟试验燃油流量原位校准系统设计与检验[J]. 燃气涡轮试验与研究,2013,26(1): 5-8,39. ZHAO Yong,HOU Minjie,CHEN Mian,et al. Design and verification of an in-situ calibration system for aero-engine fuel flow rate measurement in altitude simulation test[J]. Gas Turbine Experiment and Research,2013,26(1): 5-8,39. (in ChineseZHAO Yong, HOU Minjie, CHEN Mian, et al. Design and verification of an in-situ calibration system for aero-engine fuel flow rate measurement in altitude simulation test[J]. Gas Turbine Experiment and Research, 2013, 26(1): 5-8, 39. (in Chinese) [6] 侯敏杰,刘志友,文刚. 高空舱内次流与真空度作用对发动机台架推力测量的影响研究[J]. 航空动力学报,2005,20(3): 384-388. HOU Minjie,LIU Zhiyou,WEN Gang. Research of the secondary flow and vacuum impact on the thrust measurement[J]. Journal Of Aerospace Power,2005,20(3): 384-388. (in ChineseHOU Minjie, LIU Zhiyou, WEN Gang. Research of the secondary flow and vacuum impact on the thrust measurement[J]. Journal Of Aerospace Power, 2005, 20(3): 384-388. (in Chinese) [7] 刘志友,侯敏杰,马前容. 高度对航空发动机地面试验性能的影响[J]. 航空动力学报,2006,21(2): 381-385. LIU Zhiyou,HOU Minjie,MA Qianrong. Research of altitude effect on aero-engine ground test performance[J]. Journal of Aerospace Power,2006,21(2): 381-385. (in ChineseLIU Zhiyou, HOU Minjie, MA Qianrong. Research of altitude effect on aero-engine ground test performance[J]. Journal of Aerospace Power, 2006, 21(2): 381-385. (in Chinese) [8] 刘志友,吴锋,仇钎. 直连式高空台试验中真空度与次流作用力校准的一种新方法[J]. 燃气涡轮试验与研究,2013,26(1): 1-4. LIU Zhiyou,WU Feng,QIU Qian. A new measurement method for the action of the secondary flow and vacuum in direct-connect ATF[J]. Gas Turbine Experiment and Research,2013,26(1): 1-4. (in ChineseLIU Zhiyou, WU Feng, QIU Qian. A new measurement method for the action of the secondary flow and vacuum in direct-connect ATF[J]. Gas Turbine Experiment and Research, 2013, 26(1): 1-4. (in Chinese) [9] 焦天佑,郭昕. 高空台对比试验校准与标定技术研究[J]. 燃气涡轮试验与研究,1997,10(1): 1-7. JIAO Tianyou,GUO Xin. Research on calibration and calibration technology of high altitude platform comparison test[J]. Gas Turbine Experiment and Research,1997,10(1): 1-7. (in ChineseJIAO Tianyou, GUO Xin. Research on calibration and calibration technology of high altitude platform comparison test[J]. Gas Turbine Experiment and Research, 1997, 10(1): 1-7. (in Chinese) [10] 焦华宾,莫松. 航空涡轮发动机现状及未来发展综述[J]. 航空制造技术,2015,58(12): 62-65. JIAO Huabin,MO Song. Present status and development trend of aircraft turbine engine[J]. Aeronautical Manufacturing Technology,2015,58(12): 62-65. (in ChineseJIAO Huabin, MO Song. Present status and development trend of aircraft turbine engine[J]. Aeronautical Manufacturing Technology, 2015, 58(12): 62-65. (in Chinese) [11] 焦天佑. 涡喷涡扇发动机试车台校准方法的研究[J]. 燃气涡轮试验与研究,1999,12(4): 5-7. JIAO Tianyou. Study on calibration method of turbojet turbofan engine test bench[J]. Gas Turbine Experiment and Research,1999,12(4): 5-7. (in ChineseJIAO Tianyou. Study on calibration method of turbojet turbofan engine test bench[J]. Gas Turbine Experiment and Research, 1999, 12(4): 5-7. (in Chinese) [12] 廉筱纯,吴虎. 航空发动机原理[M]. 西安: 西北工业大学出版社,2005. LIAN Xiaochun,WU Hu. Aeroengine principle[M]. Xi’an: Northwestern Polytechnical University Press,2005. (in ChineseLIAN Xiaochun, WU Hu. Aeroengine principle[M]. Xi’an: Northwestern Polytechnical University Press, 2005. (in Chinese) [13] 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): 54-57,103. DU Heling. Measurement and determination method of aero-engine thrust[J]. Journal of Aerospace Power,1997,12(4): 54-57,103. (in ChineseDU Heling. Measurement and determination method of aero-engine thrust[J]. Journal of Aerospace Power, 1997, 12(4): 54-57, 103. (in Chinese) [14] 杜鹤龄. 航空发动机高空模拟[M]. 北京: 国防工业出版社,2002. DU Heling. Aero-engine altitude simulating[M]. Beijing: National Defense Industry Press,2002. (in ChineseDU Heling. Aero-engine altitude simulating[M]. Beijing: National Defense Industry Press, 2002. (in Chinese) [15] WU F,GONG X Q,SU J Y. Aerodynamic calibration and thrust correction method with inflow separation in indoor sea level test facility: ASME Paper GT2014-25594 [R]. Düsseldorf,Germany: ASME,2014. [16] LISTER J,BONSON W,MCAMIS R. Inlet duct static pressure assessment method contribution to direct-connect thrust measurement uncertainty: AIAA 2007-5335 [R]. Reston,US: AIAA,2007. [17] BEALE D. Experimental measurement of venturi discharge coefficient including sensitivity to geometric and flow quality variables: AIAA 1999-304 [R]. Reston,US: AIAA,1999. [18] BEALE D,HAND T,SEBOURN C. Development of a bellmouth airflow measurement technique for turbine engine ground test facilities: AIAA2001-3676 [R]. Reston,US: AIAA,2001. -