掠型设计调控跨声速离心压气机内部流动机理

李子良; 韩戈; 朱俊强; 卢新根

doi:10.13224/j.cnki.jasp.20210228

掠型设计调控跨声速离心压气机内部流动机理

doi: 10.13224/j.cnki.jasp.20210228

李子良^1,2,3,,
韩戈^1,2,3,
朱俊强^1,2,3,
卢新根^1,2,3, ,

1.
中国科学院工程热物理研究所轻型动力实验室，北京 100190
2.
中国科学院大学工程科学学院，北京 100049
3.
中国科学院轻型动力创新研究院，北京 100190

基金项目: 航空发动机及燃气轮机重大专项基础研究（2017-Ⅱ-0002-0014）

详细信息

作者简介:
李子良（1997-），男，博士生，研究领域为叶轮机械气动热力学。E-mail：liziliang2020@iet.cn

通讯作者:
卢新根（1978-），男，研究员，博士，研究领域为叶轮机械气动热力学。E-mail：luxg@iet.cn

中图分类号: V231.3
计量
- 文章访问数: 74
- HTML浏览量: 6
- PDF量: 82
- 被引次数: 0
出版历程
- 收稿日期: 2021-05-10
- 刊出日期: 2022-04-28

Mechanism of swept controlling internal flow of transonic centrifugal compressor

LI Ziliang^{1,2,3
,},
HAN Ge^1,2,3,
ZHU Junqiang^1,2,3,
LU Xingen^{1,2,3
, ,}

1.
Laboratory of Light-duty Gas-turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
2.
School of Engineering Science，University of Chinese Academy of Sciences，Beijing 100049，China
3.
Innovation Academy for Light-duty Gas Turbine，Chinese Academy of Sciences，Beijing 100190，China

摘要

摘要: 跨声速离心压气机面临进口激波控制的难题，探索前缘掠型对跨声离心压气机影响机理对于进一步提升离心压气机性能具有重要意义。以两台跨声速离心压气机为研究对象，利用经过校核的数值模拟手段探究了不同前缘掠型下压气机的性能及流场变化。结果表明：设计工况下叶轮入口的激波位置直接决定了前缘掠型设计的作用效果。掠型设计通过改变导风轮叶顶载荷分布，进而影响其通流能力，同时改变了其入口激波结构和流动损失。当叶轮入口叶顶激波呈吞入状态时，采用前缘后掠会减弱槽道激波强度，从而减小导风轮叶顶附近损失；当叶轮入口叶顶激波呈脱体状态时，采用前缘前掠会减弱前缘激波强度，使得激波更加附体，从而减小导风轮叶顶附近损失。
- 跨声速离心压气机 /
- 流动控制 /
- 前缘掠型 /
- 载荷分布 /
- 激波结构
Abstract: Transonic centrifugal compressors face the problem of shock wave controlling.Therefore，the knowledge of the flow mechanism under leading edge swept effect plays an important role in improving the transonic centrifugal compressors performance.Two different transonic centrifugal compressors were investigated by numerical simulations after verified.The results show that,the inducer inlet shock position directly determines the effect of the leading edge swept under the design point.The change of leading edge swept can affect the flow-through capacity by changing the load distribution on the tip of inducer，and furthermore change the shock structure and flow loss on the tip of the inducer.For the impellers whose passage shock wave was swallowed in the blade passages，the backward swept weakened the strength of the passage shock wave and thus reduced the loss near the blade tip of the inducer.However，for the impellers whose leading edge shock wave was detached from leading edge，the forward swept weakened the strength of the leading edge shock wave and made the shock wave more attached，thus reducing the loss near the tip of inducers.
- transonic centrifugal compressor /
- flow control /
- leading edge swept /
- loading distribution /
- shock wave structure

HTML

参考文献(18)

[1]	KRAIN H.Review of centrifugal compressor's application and development[J].Journal of Turbomachinery，2005,127（1）:25-34.
[2]	KANEKO M,TSUJITA H.Numerical investigation of influence of tip leakage flow on secondary flow in transonic centrifugal compressor at design condition[J].Journal of Thermal Science,2015,24（2）:117-122.
[3]	DENTON J D,XU L.The exploitation of three-dimensional flow in turbomachinery design[J].Proceedings of the Institution of Mechanical Engineers:Part C Journal of Mechanical Engineering Science,1998,213（2）:125-137.
[4]	OKUI H,VERSTRAETE T,BRAEMBUSSCHE R A VAN DEN,et al.Three-dimensional design and optimization of a transonic rotor in axial flow compressors[J].Journal of Turbomachinery,2013,135（3）:031009.1-031009.11.
[5]	VAD J.Aerodynamic effects of blade sweep and skew in low-speed axial flow rotors at the design flow rate:an overview[J].Proceedings of the Institution of Mechanical Engineers:Part A Journal of Power and Energy,2008,222（1）:69-85.
[6]	HAZBY H,ROBINSON C,CASEY M,et al.Free-form versus ruled inducer design in a transonic centrifugal impeller[J].Journal of Turbomachinery,2018,140（1）:011010.1-011010.12.
[7]	ELFERT M,WEBER A,WITTROCK D,et al.Experimental and numerical verification of an optimization of a fast rotating high-performance radial compressor impeller[J].Journal of Turbomachinery,2017,139（10）:101007.1-101007.9.
[8]	WITTROCK D,JUNKER M,BEVERSDORFF M,et al.A deep insight into the transonic flow of an advanced centrifugal compressor design[R].ASME Paper GT2019-90308，2019 .
[9]	HE Xiao,ZHENG Xinqian.Mechanisms of sweep on the performance of transonic centrifugal compressor impellers[J].Journal of Propulsion and Power，2016，32（5）:1220-1229.
[10]	陈思成.跨声速离心压气机的掠叶片设计技术研究[D].北京：北京理工大学,2016.
[11]	郭龙凯,刘艳明,郑新前,等.混合型前缘掠对离心压气机气动性能的影响[J].内燃机学报,2016,34（3）:281-287.
[12]	RODGERS C.The centrifugal compressor inducer[R].ASME Paper 98-GT-032，1998.
[13]	RODGERS C.High specific speed,high inducer tip Mach number,centrifugal compressor[R].ASME Paper GT2003-38949，2003.
[14]	PALMER D L,WATERMAN W F.Design and development of an advanced two-stage centrifugal compressor[R].ASME Paper 94-GT-202，1994.
[15]	ERDMENGER R R,MICHELASSI V.Impact of main and splitter blade leading edge contour on the performance of high pressure ratio centrifugal compressors[R].ASME Paper GT2014-27062，2014.
[16]	GANESH C S,NAGPURWALA Q,DIXIT C.Effect of leading edge sweep on the performance of a centrifugal compressor impeller[J].SASTech-Technical Journal of RUAS,2010,9（2）:55-62.
[17]	LI Z,HAN G,LU X,et al.Improving the operating range using a centrifugal compressor with a tandem impeller[EB/OL].[2021-05-05].https:∥www.sciencedirect.com/science/article/pii/S1270963819316165.
[18]	ROCHUON N.Analyse de l'écoulement tridimensionnel et instationnaire dans un compresseur centrifuge à fort taux de pression[D].Ecully,France:Ecole Centrale de Lyon,2007.