Aerodynamic moment analysis of first stage variable stator vanes of single⁃stage transonic compressor in surge exit process

Delong LIU; Haining GUO; Haibao YIN; Dejun MENG

doi:10.7527/S1000-6893.2023.28550

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2023 , Vol. 44 >Issue 24: 128550 - 128550

DOI: https://doi.org/10.7527/S1000-6893.2023.28550

Fluid Mechanics and Flight Mechanics

Aerodynamic moment analysis of first stage variable stator vanes of single⁃stage transonic compressor in surge exit process

Delong LIU ,
Haining GUO ,
Haibao YIN ,
Dejun MENG

Expand

Shenyang Engine Research Institute，Aero-Engine Corporation of China，Shenyang 110015，China

E-mail： ldl020310323@sina.com

Received date: 2023-02-13

Revised date: 2023-02-28

Accepted date: 2023-06-07

Online published: 2023-06-21

Supported by

National Level Project

Fold

Cite this article

Delong LIU , Haining GUO , Haibao YIN , Dejun MENG . Aerodynamic moment analysis of first stage variable stator vanes of single⁃stage transonic compressor in surge exit process[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(24) : 128550 -128550 . DOI: 10.7527/S1000-6893.2023.28550

References

1	LI Y L， SAYMA A. Numerical investigation of VSVs Mal-Schedule effects in a three stage axial compressor： GT2014-25145［R］. New York： ASME， 2014.
2	BENSER W A. Aerodynamic design of axial-flow compressors， chapter XIII compressor operation with one or more blade rows stalled： NASA SP-36［R］. Washington， D.C.： NASA， 1965.
3	HOWE D C， MARCHANT R D. Energy efficient engine high-pressure compressor test hardware detailed design： NASA CR-180850［R］. Washington， D.C.： NASA， 1988.
4	HOLLOWAY P R， KNIGHT G L， KOCH C C， et al. Energy efficient engine high-pressure compressor detailed design report： NASA CR-165558［R］. Washington， D.C.： NASA； 1973.
5	唐智明，詹孟萱. 高效节能发动机文集：第三分册风扇压气机设计与试验［M］∥ 北京：航空工业出版社， 1991： 196.
	TANG Z M， ZHAN M X. Energy efficient engine collection of essays： Volume 3 fan and compressor design and test［M］∥ Beijing： Aviation Industry Press， 1991： 196 （in Chinese）.
6	梁钧襄，侯志兴. 高效节能发动机文集：第八分册控制系统设计［M］∥ 北京：航空工业出版社， 1991： 5-23.
	LIANG J X， HOU Z X. Energy efficient engine collection of essays： Volume 8 control system design［M］∥ Beijing： Aviation Industry Press， 1991： 5-23 （in Chinese）.
7	刘太秋，赵月振，王咏梅，等. 负荷系数0.5的高负荷单级轴流压气机设计及试验研究［J］. 航空发动机， 2022， 48（5）： 1-39.
	LIU T Q， ZHAO Y Z， WANG Y M， et al. Design and experimental investigation of a highly loaded single-stage axial compressor with loading coefficient of 0.5［J］. Aeroengine， 2022， 48（5）： 1-39 （in Chinese）.
8	SCHULZE G， BLAHA C， HENNECKE D K. The performance of a new axial single stage transonic compressor： ISABE 95-7072［R］. Reston： AIAA， 1995.
9	PAULON J， BEDOT J C， ZHANG Z， et al. Design and test results of a high performance single stage compressor： ISABE 91-7071［R］. Reston： AIAA， 1991.
10	MOORE R D， REID L. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78， respectively， and with design pressure ratio of 1.82： NASA N82-19222［R］. Washington， D.C.： NASA， 1982.
11	WADIA A R， SZUCS P N， CRALL D W. Inner workings of aerodynamic sweep［J］. Journal of Turbomachinery， 1998， 120（4）： 671-682.
12	DARJI A P， ALONE D B， MISTRY C S. Flow studies on a single stage transonic axial flow compressor retrofitted with circumferential grooves and varied rotor-stator axial gap： GTINDIA2017-4592［R］. New York： ASME， 2017.
13	DINH C T， MA S B， KIM K Y. Effects of a circumferential feed-back channel on aerodynamic performance of a single-stage transonic axial compressor： GT2017-63536［R］. New York： ASME， 2017.
14	HAH C， HATHAWAY M， KATZ J. Investigation of unsteady flow field in a low-speed one and a half stage axial compressor： Effects of tip gap size on the tip clearance flow structure at near stall operation： GT2014-27094［R］. New York： ASME， 2014.
15	MAILACH R， MüLLER L， VOGELER K. Rotor-stator interactions in a four-stage low-speed axial compressor part II： Unsteady aerodynamic forces of rotor and stator blades： ASME GT2004-53099［R］. New York： ASME， 2004.
16	李绍斌，苏杰先，冯国泰，等. 高负荷跨声速压气机动静叶干扰下叶片气动负荷研究［J］. 推进技术， 2006， 27（5）： 410-415.
	LI S B， SU J X， FENG G T， et al. Investigation of the unsteady aerodynamic blade loads in a highly loaded transonic compressor stage［J］. Journal of Propulsion Technology， 2006， 27（5）： 410-415 （in Chinese）.
17	AOTSUKA M， WATANABE T， MACHINA Y. Role of shock and boundary layer separation on unsteady aerodynamic characteristics of oscillating transonic cascade： ASME GT2013- 38425［R］. New York： ASME， 2013.
18	RABE D， BOLCS A， RUSSLER P. Influence of inlet distortion on transonic compressor blade loading： AIAA- 1995-2461［R］. Reston： AIAA， 1995.
19	SAHAI V， CHENG D Y. New airfoil design to extend gas turbine compressor surge margin： ASME GT2003- 38209［R］. New York： ASME， 2003.
20	毛明明，宋彦萍，王仲奇. 弯掠动叶对跨声压气机非定常气动负荷的影响［J］. 工程热物理学报， 2008， 29（12）： 2033-2036.
	MAO M M， SONG Y P， WANG Z Q. Effect of curved rotor on unsteady aerodynamic loading in a transonic compressor［J］. Journal of engineering thermophysics， 2008， 29（12）： 2033-2036 （in Chinese）.
21	张鑫. 核心机驱动风扇级的气动设计及其与下游部件的匹配［D］. 北京：北京航空航天大学， 2011： 12-16.
	ZHANG X. Aerodynamic design of the CDFS and the matching of CDFS with downstream componets ［D］. Beijing： Beijing University of Aeronautics and Astronautics， 2011： 12-16 （in Chinese）.

Options

Outlines

模态框（Modal）标题

Cite this article

References