|Table of Contents|

Numerical study on the influence of supersonic pressure probe structure on measurement accuracy(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2021年04期
Page:
37-45
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical study on the influence of supersonic pressure probe structure on measurement accuracy
Author(s):
YANG Bo1LI Longfei2WU jianhong3MA Hu1*ZHOU Shengbing4
(1.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China 2.Xian Aerospace Propulsion Institute,Xian 710100,China 3.Beijing Great Wall Institute of Metrology and testing technology,AVIC,Beijing 100095,China 4.College of Aerospace Engineering,Chongqing University,Chongqing 400044,China)
Keywords:
numerical simulation total pressure probe static pressure probe supersonic
PACS:
O354.3
DOI:
-
Abstract:
The objective is to explore the influence of the opening form of the total pressure probe and static pressure probe in the supersonic flow on its measurement accuracy,and to obtain the high-precision total pressure probe and static pressure probe structure parameters.In this paper,FLUENT commercial software is used to study the performance of the total pressure probe with three opening forms:inner chamfer,hemispherical head,and outer chamfer under the conditions of seven incoming flow Mach numbers and three incoming flow deflection angles.In addition,the performance of three open-shaped static pressure probes under seven flow Mach number conditions is studied.The research results show that the numerical simulation results are in good agreement with the wind tunnel experimental results,which verifies the reliability of the numerical method.The comparison between the numerical simulation results and the theoretical value shows that the disturbance degree of the flow field by the total pressure probe is positively correlated with the accuracy of the total pressure probe.The total pressure probe with external chamfer has the best insensitivity to the installation deflection,and the relative error is less than 1.5%.The chamfer size of the total pressure probe with external chamfer has almost no effect on itsperformance.Under the conditions given in this article,the static pressure probe with a 0.2D measuring hole and a 15°angle of inclined hole can get higher-precision results.

References:

[1] 蒋浩康,马宏伟.压气机转子三维紊流流场[J].工程热物理学报,1998,19(3):287-292.
[2] 陈浮,赵桂杰,宋彦萍,等.叶片弯、掠对压气机端壁流动的影响[J].工程热物理学报,2004,25(2):211-215.
[3] 王洪伟,蒋浩康,陈懋章.大小叶片压气机平面叶栅试验研究[J].工程热物理学报,2006,27(S1):113-116.
[4] 马宏伟,贺象,单晓明,等.一种测量跨声速多级压气机转子出口二维流场的方法[J].推进技术,2013,34(6):754-759.
[5] WANG Z Q,LU B,ZHANG C K,et al.Flow field measurement in multi-stage axial compressor stator by using multi-hole pneumatic probes[J].International Journal of Turbo & Jet-Engines,2017,34(1):81-94.
[6] 熊兵,陈洪敏,文璧,等.基于四孔压力探针技术的涡轮转子出口流场测量[J].燃气涡轮试验与研究,2012,25(S1):6-10.
[7] 张晓东,姜正礼,赵旺东.五孔探针在涡轮导向器出口流场测量中的应用[J].燃气涡轮试验与研究,2010,23(4):44-48.
[8] 何中伟,Dr.SislianJP,DechambaultRL.新型高超音速静压探针的设计和实验[J].推进技术,1992,13(6):51-58.
[9] 陈武,侯安平,郑新前,等.在大分离区内使用三孔探针测试的探索[J].流体力学实验与测量,2003,17(3):84-87.
[10] 张有,吴锋,冯旭栋,等.1种副孔正交型超声速5孔探针的设计与应用[J].航空发动机,2018,44(5):65-72.
[11] 赵彬,赵俭.超音速条件下基于CFD的压力探针校准特性数值模拟[J].计测技术,2017,37(2):15-18.
[12] 沈天荣,刘海涌,刘松龄,等.风洞七孔压力探针的校准技术[J].风机技术,2006,48(4):15-19.
[13] GERNER A,MAURER C.Calibration of seven-hole probes suitable for high angles in subsonic compressible flows[C]//20th Aerospace Sciences Meeting.Orlando,FL.Reston,Virginia:AIAA,1982.
[14] EVERET T K,DURSTON D.Theory and calibration of non-nulling seven-hole cone probes for usein complex flow measurement[C]//20th Aerospace Sciences Meeting.Orlando,FL.Reston,Virginia:AIAA,1982.
[15] THOMPSON S,HACKETT J.Range extension for seven-holed probes[C]//36th AIAA Aerospace Sciences Meeting and Exhibit.Reno,NV,Reston,Virigina:AIAA,1998.
[16] WENGER C W,DEVENPORT W J.Seven-hole pressure probe calibration method utilizing look-up error tables[J].AIAA Journal,1999,37(6):675-679.
[17] 白亚磊,明晓,丁涛.七孔探针可压缩流场测量研究[J].实验力学,2010,25(6):667-672.
[18] 左泽敏,武瑞娟,郭斌.某型航空发动机高温总压探针基础激励疲劳寿命研究[J].机械强度,2015,37(2):355-359.
[19] 熊建军,倪章松,李昱,等.防冰总压/静压探针结构及控制系统设计与应用[J].测控技术,2019,38(4):132-137.
[20] 祖孝勇,张林,肖斌,等.3m?结冰风洞总压探针和皮托管研制[J].实验流体力学,2016,30(4):76-80.
[21] 姚程.超音速进气道流固耦合振动研究[D].哈尔滨:哈尔滨工业大学,2015.

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