��Ҷ�Ƕȵ��ڶ��ѹ��Ż��

ժҪ ��ʷ��ѹ��׼��ά��,��ҶƬ��ǰ��Ե��м��ü��վ,ʹ��;��ѹ��ṹ�ص�,��չ��ʺ��Լ��ʧ��ģ�ͼ��;��Լ��뵼��Ҷ�Ƕ��Ż��ڷ��,ȷ��ͬ��ת��,��Ҷ��ѵ��ڽǶ��.��90%��ת��,��Ч�ʵ㴦,��ȫ��ά��ֵģ��ֶη��ѹ��Ҷ��ѽǶȵ��ǰ��ṹ�仯.�о��:��Ҷ�Ƕȵ��ѹ��ҶƬ��еļ��ǿ��,��ʧ,ͬʱ��ķ��,��Ը��ѹ��ṹ.

	Service

	�ѱ��Ƽ��
	��ҵ��
	��ù��
	Email Alert
	RSS
	��
	��־��
	��
	��ΰ

�ؼ���� Ҷ�Ƕȵ�� ѹ�� ʧģ�� ģ��

Abstract�� The quasi-three dimensional flow fields of axial-centrifugal compressor were solved with the streamline curvature method. Calculating stations were set in the leading edge, trailing edge and the middle of blade row. The streamline locations were fitted by cubic spline curves at each iteration computation. Performance calculation codes with loss and deviation angle models were developed by using the methods mentioned above. Available loss and deviation angle models were selected by considering the special configuration of axial-centrifugal compressor. At different rotational speed, optimum angles of IGV and stator one were determined by stator vane angle adjustment method and performance analysis codes of axial-centrifugal compressor. At 90% design speed, peak efficiency, three-dimensional numerical simulations were performed for detail flow field analysis of axial-centrifugal compressor. Research results indicate that stator vane angle adjustment can weaken the intensity of shock wave, decrease the loss, prevent the air flow deviation of the blade surface, and improve the performance of axial-centrifugal compressor.

Keywords�� stator setting angles adjustment axial-centrifugal compressor loss model deviation angle model performance curve

Received 2006-10-20;

About author: ��־��(1977-),��,�Ĵ��,��ʿ��,cao_zp@163.com.

��ñ��:

��־��, �� , �� ΰ.��Ҷ�Ƕȵ��ڶ��ѹ��Ż��[J] ��պ��ѧѧ��, 2007,V33(08): 878-881

Cao Zhipeng, Liu Bo, Ding Wei.Stator setting angles adjustment on performance improvement of axial-centrifugal compressor[J] JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2007,V33(08): 878-881

��ӱ��:

http://bhxb.buaa.edu.cn//CN/ �� http://bhxb.buaa.edu.cn//CN/Y2007/V33/I08/878

[1]	Steinke Ronald J. Design of 9.271-pressure-ratio 5-stage core compressor and overall performance for first 3 stages .NASA-TP-2597,1986
[2]	��. �༶��ѹ��Ҷת��Ż��[J]. ��ն��ѧ��, 1992,7(1):77-80 Wang Yongming. Stator angle reset optimization computation of multi-stage axial-flow compressor[J]. Journal of Aerospace Power,1992,7(1):77-80(in Chinese)
[3]	�Ž�,��. ��Ҷ�Ƕȵ��ڶ�ѹ��Ӱ��о�[J]. ��ն��ѧ��,2000,15(1):27-30 Zhang Jian, Ren Minglin. Experimental investigation on effect of stator vane angle adjustment on compressor performance[J]. Journal of Aerospace Power,2000,15(1):27-30(in Chinese)
[4]	��Ǵ�. ת��Ż��ڵ�ѹ��ѹ��ϵ�Ӧ��[J]. ȼ��о�,1998,11(4):6-14 Fan Feida. Application of angle reset optimization program on low pressure-ratio axial-flow compressor[J].Gas Turbine Experiment and Research,1998,11(4):6-14(in Chinese)
[5]	��,��,��Ǵ�. �༶ѹ��ɵ��Ҷת�ǵĶ�Ŀ��Ż��о�[J]. �ƽ��,1997,18(4):26-30 Song Wenyan, Li Xin, Fan Feida. Investigation on multi-objective optimizing angle of variables stator of axial-flow compressor[J]. Journal of Propulsion Technology,1997,18(4):26-30(in Chinese)
[6]	��ǰ��. �༶��ѹ��ܵ��ֵԤ��[J]. ��ն��ѧ��,2004,19(1):108-112 Liu Qianzhi. Numerical prediction of multi-stage axial flow compressor off-design performances[J]. Journal of Aerospace Power,2004,19(1):108-112(in Chinese)
[7]	Denton, J D. The calculation of three-dimensional viscous flow through multistage turbomachines[J].ASME Journal of Turbomachinery.1992,114:18-26
[8]	Adamczyk J J. Aerodynamic analysis of multistage turbomachinery flows in support of aerodynamic design . NASA-19990116700,1999
[9]	��, ��. ��/��ѹ��ֵģ��[J]. �ƽ��, 2005, 26(6):522-525 Li Xiaojuan, Gui Xingmin. Numerical simulation of fan/compressor design and off-design performance[J]. Journal of Propulsion Technology,2005,26(6):522-525(in Chinese)
[10]	Ҧ��.��ʽѹ��Ʒ��о� .��:��ҵ��ѧ��ն��ܹ��ϵ.[J].1992 Yao Jixian. Research of aerodynamic design methods on axial-flow compressor .Xi’an:Dept of Aeroengine and Thermal Power Engineering, Northwestern Polytechnical University.1992,:-