Assessment and measurement of total pressure distortion based on five-hole-probe for S-shaped inlet

Xu Zhulin; Gao Rongzhao; Da Xingya

doi:10.11729/syltlx20170130

Volume 32 Issue 4

Turn off MathJax

Article Contents

Abstract

References

Journal of Experiments in Fluid Mechanics > 2018 > 32(4): 78-86. > DOI: 10.11729/syltlx20170130

Xu Zhulin, Gao Rongzhao, Da Xingya. Assessment and measurement of total pressure distortion based on five-hole-probe for S-shaped inlet[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(4): 78-86. DOI: 10.11729/syltlx20170130

Citation:

PDF (16907 KB)

Assessment and measurement of total pressure distortion based on five-hole-probe for S-shaped inlet

High Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

More Information

Received Date: September 28, 2017
Revised Date: May 13, 2018

Graphical Abstract

Abstract

Abstract

The assessment and measurement of total pressure distortion of the inlet is significant in the assessment of the integration of the inlet and engine. S-shaped inlet possesses great stealth performance, but the complex fluid field in the outlet contributes to error in the measurement and assessment, which impedes the integration of the inlet and engine. The experimental results show that the sector fitting is suitable for data processing of total pressure in the S-shaped inlet. The circumferential total pressure distortion index increases from 0.005 to 0.09 while the maximum radial index not exceeding 0.055 with the increase of Mach number from 0.2 to 0.6. The higher Mach number is, the severer total pressure distortion is. Total pressure recovery index of the main area of total pressure distortion in outlet is below 0.85. In total, compared with numerical computation and the rake measurement, the results of five-hole-probe measurement are more comprehensive and rational.
- S-shaped inlet,
- five-hole-probe,
- total pressure measurement,
- total pressure distortion,
- data processing

FullText(HTML)

References (28)

References

[1]	Yang H, Li F, Song Y Y, et al. Numerical investigation of Electrohydrodynamic(EHD) flow control in an S-shaped duct[J]. Plasma Science and Technology, 2012, 14(10):897-904. DOI: 10.1088/1009-0630/14/10/08
[2]	Da X Y, Fan Z L, Fan J C, et al. Microjet flow control in an ultra-compact serpentine inlet[J]. Chinese Journal of Aeronautics, 2015, 28(5):1381-1390. DOI: 10.1016/j.cja.2015.07.008
[3]	屠宝锋, 胡骏, 张凯.对涡旋流影响压气机转子性能和稳定性的研究[J].推进技术, 2016, 37(4):640-645. http://d.old.wanfangdata.com.cn/Periodical/tjjs201604006 Tu B F, Hu J, Zhang K. Effects of twin swirl on performance and stability of compressor rotor[J]. Journal of Propulsion Technology, 2016, 37(4):640-645. http://d.old.wanfangdata.com.cn/Periodical/tjjs201604006
[4]	Beale D K, Zelenak M. Development and validation of a free jet technique for inlet-engine compatibility testing[R]. AIAA-1992-3921, 1992.
[5]	Kimzey W F. An investigation and calibration of a device for the generation of turbulent flow at the inlet of a turbojet engine[R]. AEDC-TR-65-195, 1965.
[6]	Oates G C, Sherman D A, Motycka D L. Experimental study of inlet-generated pressure fluctuations[R]. AFAPL-TR-70-103, 1970.
[7]	Plourde G A, Brimelow B. Pressure fluctuations cause compressor instability[R]. AFAPL-TR-70-103, 1970.
[8]	Younghans J L, Moore M T, Collins T P, et al. Inlet flow field simulation techniques for engine/compressor testing[R]. AIAA-970-591, 1970.
[9]	Anderson R E. Aircraft engine inlet pressure distortion testing in a ground test facility[R]. AIAA-1983-1233, 1983.
[10]	Kutschenreuter P H, Collins T P, Vier I W. P 3G-a new dynamic distortion generator[R]. AIAA-73-1317, 1973.
[11]	Overall B W, Harper R E. The airjet distortiongenerator system-a new tool for aircraft turbine engine testing[R]. AIAA-1977-993, 1977.
[12]	Beale D, Cramer K, King P. Development of improved methods for simulating aircraft inlet distortion in turbine engine ground test[R]. AIAA-2002-3045, 2002.
[13]	Yuhas A J, Ray R J, Burley R R, et al. Design and development of an F/A-18 inlet distortion rake: a cost and time saving solution[R]. NASA-TM-4722, 1995.
[14]	姜健, 于芳芳, 赵海刚, 等.进气道/发动机相容性评价体系的完善与发展[J].科学技术与工程, 2009, 21(9):6474-6483. DOI: 10.3969/j.issn.1671-1815.2009.21.041 Jiang J, Yu F F, Zhao H G, et al. Perfection and development of engine/intake compatibility evaluate criterion[J]. Science Technology and Engineering, 2009, 9(21):6474-6483. DOI: 10.3969/j.issn.1671-1815.2009.21.041
[15]	刘大响, 叶培梁.俄罗斯的发动机进口流场畸变评定指南[J].燃气涡轮试验与研究, 1994, 4(3):436-441. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK199400385119
[16]	郁新华, 刘斌, 陶于金, 等.背负式进气道设计及其气动性能研究[J].西北工业大学学报, 2007, 25(2):270-273. DOI: 10.3969/j.issn.1000-2758.2007.02.024 Yu X H, Liu B, Tao Y J, et al. Top-mounted inlet design and its aerodynamic performance[J]. Journal of Northwestern Polytechnical University, 2007, 25(2):270-273. DOI: 10.3969/j.issn.1000-2758.2007.02.024
[17]	Stoll F, Tremback J W, Arnaiz H H. Effect of number of probes and their orientation on the calculation of several compressor face distortion descriptors[R]. NASA-TM-72859, 1979.
[18]	Lawley T, Price D. A miniature three-dimensional pressure probe[J]. Review of Scientific Instruments, 1971, 42(1):158-160. DOI: 10.1063/1.1684855
[19]	吴岳庚.当代压气机试验与测试技术[J].科技与实践, 1998, 2:30-39.
[20]	Gilarranz J L, Ranz A J, Kopko J A, et al. On the use of five-hole probes in the testing of industrial centrifugal compressors[J]. ASME Journal of Turbomachinery, 2004, 127(1):91-106. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=d15a56ae65936e06b09d126bea378e61
[21]	姜健, 屈霁云, 赵海刚, 等.进气道旋流模拟及测量地面试车台试验研究[J].燃气涡轮试验与研究. 2012, 25(3):36-39. http://d.old.wanfangdata.com.cn/Periodical/rqwlsyyyj201203009 Jiang J, Qu J Y, Zhao H G, et al. Simulation and measurement of inlet swirl in ground test bed[J]. Gas Turbine Experiment and Research, 2012, 25(3):36-39. http://d.old.wanfangdata.com.cn/Periodical/rqwlsyyyj201203009
[22]	江勇, 陶增元, 张发启, 等.某型飞机进气道与发动机地面匹配实验研究[J].航空动力学报, 2003, 18(4):554-557. DOI: 10.3969/j.issn.1000-8055.2003.04.021 Jiang Y, Tao Z Y, Zhang F Q, et al. Matching test of an aircraft inlet and engine on the ground[J]. Journal of Aerospace Power, 2003, 18(4):554-557. DOI: 10.3969/j.issn.1000-8055.2003.04.021
[23]	Society of automotive engineers. Gasturbine engine inlet flow distortion guidelines[R]. ARP-2002-1420, 2002.
[24]	AllianTech S. A. S. Multi-hole velocity probes[S]. Gennevilliers: Aeroprobe Corporation, 2010.
[25]	Johansen E S, Rediniotis O K, Jones G. The compressible calibration of miniature multi-hole probes[J]. ASME Journal of Fluids Engineering, 2001(123):128-138. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=8371b029b458db82798e44c2ddbe4d98
[26]	Ramakrishnan V, Rediniotis O K. Calibration and data reduction algorithms for non-conventional multi-hole pressure probes[J]. International Journal of English Studies, 2004, 12(5):133-150.
[27]	Society of automotive engineers. A methodology for assessing inlet swirl distortion[R]. ARP-2010-5686, 2010.
[28]	徐诸霖, 达兴亚, 范召林, 等.基于五孔探针的大S弯进气道旋流畸变评估[J].航空学报, 2017, 38(12):48-57. http://d.old.wanfangdata.com.cn/Periodical/hkxb201712005 Xu Z L, Da X Y, Fan Z L, Assessment of swirl distortion of serpentine inlet based on five-hole-probe[J]. Acta Aeronautica ET Astronautica Sinica, 2017, 38(12):48-57. http://d.old.wanfangdata.com.cn/Periodical/hkxb201712005

Cited By

Cited by

Periodical cited type(2)

1.	车兵辉，魏然，曾伟. 风洞CTS试验六自由度机构控制方法研究. 计算机测量与控制. 2018(12): 84-88 .
2.	贺云，张飞龙，徐志刚，刘哲. 一种基于风洞试验环境的轨迹捕获系统设计. 兵工学报. 2018(12): 2480-2487 .

Other cited types(2)

Get Citation

PDF

XML

Article Metrics

Article views (136) PDF downloads (10) Cited by(4)

Assessment and measurement of total pressure distortion based on five-hole-probe for S-shaped inlet

Abstract

References

Cited by

Periodical cited type(2)

Other cited types(2)

Catalog

Article Metrics

Related

Assessment and measurement of total pressure distortion based on five-hole-probe for S-shaped inlet

Abstract

References

Cited by

Periodical cited type(2)

Other cited types(2)

Catalog

Article Metrics

Related

Export File

Citation

Format

Content