An inlet flow model of swept blades for streamline curvature through-flow methods

CHANG Hao; JIN Donghai; GUI Xingmin

doi:10.7527/S1000-6893.2017.21616

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2018 , Vol. 39 >Issue 3: 121616 - 121616

DOI: https://doi.org/10.7527/S1000-6893.2017.21616

Fluid Mechanics and Flight Mechanics

An inlet flow model of swept blades for streamline curvature through-flow methods

CHANG Hao ,
JIN Donghai ,
GUI Xingmin

Expand

1. AECC Shenyang Engine Research Institute, Shenyang 110015, China;
2. School of Energy and Power Engineering, Beihang University, Beijing 100083, China

Received date: 2017-07-19

Revised date: 2017-11-08

Online published: 2017-11-08

Fold

Abstract

As a designing technique, blade sweep is currently widely utilized in the design of axial fans/compressors. The flow mechanisms of blade sweep has been extensively studied. In recent years, many studies have reported the incidence variation due to sweep, which can be attributed to the alteration of inlet radial equilibrium and axial velocity distributions induced by blade sweep. An inlet flow model of swept blades for streamline curvature through-flow methods is developed. The model takes into account the variation of inlet radial equilibrium due to blade sweep, without the hypothesis that the flow is uniform in the circumferential direction at the blade inlet. The model is applied for the design of a subsonic swept rotor blade, and the results show that in comparison with the original calculation, the model proposed can predict the distribution of axial velocity as well as the incidence angle more precisely. Therefore, the accuracy of design is improved with the model. Moreover, the effect of blade sweep on inlet radial pressure equilibrium is quantitatively analyzed.

Key words： swept blades; angle of attack; streamline curvature method; radial equilibrium; blade force; compressor

Cite this article

CHANG Hao , JIN Donghai , GUI Xingmin . An inlet flow model of swept blades for streamline curvature through-flow methods[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018 , 39(3) : 121616 -121616 . DOI: 10.7527/S1000-6893.2017.21616

References

[1] SMITH L H, YEH H. Sweep and dihedral effect in axial flow turbomachinery[J]. ASME Journal of Basic Engineering, 1963, 85(3):401-414.
[2] BEATTY L A, SAVAGE M, EMERY J C. Low speed cascade tests of two 45 degree swept compressor blades with constant spanwise loading:NACA RM-L53L07[R].Washington,D.C.:NACA, 1954.
[3] GOODWIN W R. Effect of sweep on performance of compressor blade sections as indicated by swept blade rotor, unswept blade rotor and cascade tests:NACA TN-4062[R]. Washington,D.C.:NACA, 1957.
[4] LEWIS R I, HILL J M. The influence of sweep and dihedral in turbomachinery blade rows[J]. Journal of Mechanical Engineering Science, 1971, 13(4):266-285.
[5] BLISS D B, HAYDEN R E, MURRAY B S, et al. De-sign considerations for a novel low source noise transonic fan stage:AIAA-1976-0577[R]. Reston,VA:AIAA, 1976.
[6] LUCAS R G, WOODARD R P, MACKINNON M J. Acoustic evaluation of a novel swept-rotor fan:AIAA-1978-1121[R]. Reston,VA:AIAA, 1978
[7] NEUBERT R J, HOBBS D E, WEINGOLD H D. Application of sweep to improve the efficiency of a transonic fan:Part I-design[J]. Journal of Propulsion and Power, 1995, 11(1):49-54.
[8] HAH C, WENNERSTROM A J. Three-dimensional flow-fields inside a transonic compressor with swept blades[J]. Journal of Turbomachinery, 1991, 113(2):241-251.
[9] COPENHAVER W W, HAH C, PUTERBAUGH S L. Three-dimensional flow phenomena in a transonic, high-through-flow, axial-flow compressor stage[J]. Journal of Turbo-machinery, 1993, 115(2):240-248.
[10] PUTERBAUGH S L, COPENHAVER W W, HAH C, et al. A three-dimensional shock loss model applied to an aft-swept, transonic compressor rotor[J]. Journal of Turbomachinery, 1997, 119(3):452-459.
[11] WADIA R, SZUCS P N, CRALL D W. Inner workings of aerodynamic sweep[J]. Journal of Turbomachinery, 1998, 120(4):671-682.
[12] HAH C, PUTERBAUGH S L, WADIA A R. Control of shock structure and secondary flow field inside transonic compressor rotors through aerodynamic sweep:ASME 98-GT-561[R]. New York:ASME, 1998
[13] WADIA A R, SZUCS P N, NISKODE P N, et al. Forward-swept rotor blade:US Patent No. 5167489[P].1992-12-01.
[14] WADIA A R, SZUCS P N, CRALL D W, et al. Forward swept rotor studies in multistage fans with inlet distortion[C]//ASME Turbo Expo 2002:Power for Land, Sea, and Air. New York:ASME, 2002:11-21
[15] DENTON J D, XU L. The effects of lean and sweep on transonic fan performance:GT-2002-30327[R]. New York:ASME, 2002.
[16] BLAHA C, KABLITZ S, HENNECKE D K, et al. Numerical investigation of the flow in an aft-fwept transonic compressor rotor[C]//ASME Turbo Expo 2000:Power for Land, Sea, and Air. New York:ASME,2000.
[17] KABLITZ S, BERGNER J, HENNECKE D K, et al. Darmstadt rotor No. 2, Ⅲ:Experimental analysis of an aft-swept axial transonic compressor stage[J]. International Journal of Rotating Machinery, 2003, 9(6):393-402.
[18] PASSRUCKER H, ENGBER M, KABLITZ S, et al. Effect of forward sweep in a transonic compressor rotor[J]. Proceedings of the Institution of Mechanical Engineers, Part A:Journal of Power and Energy, 2003, 217(4):357-365.
[19] BERGNER J, KABLITZ S, HENNECKE D K. Influence of sweep on the 3D shock structure in an axial transonic compressor:GT2005-6883[R]. New York:ASME, 2005.
[20] GUNARAJ J, HANSON D, HAYES J, et al. A comparison of two fan stage designs with different rotor leading edge sweep:GT2014-27218[R]. New York:ASME, 2014.
[21] BENINI E, BIOLLO R. Aerodynamics of swept and leaned transonic compressor-rotors[J]. Journal of Applied Energy, 2007, 84(10):1012-1027.
[22] AMANO R, XU C. Blade sweep effects of turbomachinery:AIAA-2005-0048[R].Reston,VA:AIAA, 2005.
[23] YAMAGUCHI N, TOMINAGA T, HATTORI S, et al. Secondary-loss reduction by forward-skewing of axial compressor rotor blading[J]. Proceedings of Yokohama International Gas Turbine Congress, 1991, V2:61-68.
[24] GUMMER V, WENGER U, KAU H P. Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressor[J]. Journal of Turbomachinery, 2001,123(1):40-48.
[25] 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.
[26] GOVARDHAN M, KUMAR O G K, SITARAM N. Computational study of the effect of sweep on the performance and flow field in an axial flow compressor rotor[J]. Proceedings of the Institution of Mechanical Engineers, Part A:Journal of Power and Energy, 2007, 221(3):315-329.
[27] RAMAKRISHNA P V, GOVARDHAN M. Combined effects of forward sweep and tip clearance on the performance of axial flow compressor Stage:GT2009-59840[R]. New York:ASME, 2009.
[28] RAMAKRISHNA P V, GOVARDHAN M. Study of sweep and induced dihedral effects in subsonic axial flow compressor passages-Part I:Design considerations-changes in incidence, deflection, and streamline curvature[J]. International Journal of Rotating Machinery, 2009:1-10.
[29] RAMAKRISHNA P V, GOVARDHAN M. Numerical study of the stagger angle effects in forward swept axial compressor rotor passages:GT2010-23160[R]. New York:ASME, 2010.
[30] VAD J, KWEDIKHA A R A, JABERG H. Effects of blade sweep on the performance characteristics of axial flow turbomachinery rotors[J]. Proceedings of the Institution of Mechanical Engineers, Part A:Journal of Power and Energy, 2006, 220(7):737-749.
[31] MCNULTY G S, KHALID S A, DECKER J J, et al. The impact of forward swept rotors on tip clearance flows in subsonic axial compressors[J]. Journal of Turbomachinery, 2004, 126(4):445-454.
[32] LI Y, LIU J, OUYANG H, et al. Internal flow mechanism and experimental research of low pressure axial fan with forward-skewed blades[J]. Journal of Hydrodynamics, 2008, 20(3):299-305.
[33] VAD J, KWEDIKHA A R A, HORVATH C, et al. Aerodynamic effects of forward blade skew in axial flow rotors of con-trolled vortex design[J]. Proceedings of the Institution of Mechanical Engineers, Part A:Journal of Power and Energy, 2007, 221(7):1011-1023.
[34] ILIKAN A N, AYDER E. Influence of the sweep stacking on the performance of an axial fan[J]. Journal of Turbo-machinery, 2015, 137(6):061004.
[35] GUI X M, ZHU F, WAN K, et al. Effects of inlet circumferential fluctuation on the sweep aerodynamic performance of axial fans/compressors[J]. Journal of Thermal Science, 2013, 22(5):32-41.
[36] CHANG H, ZHU F, JIN D, et al. Effect of blade sweep on inlet flow in axial compressor cascades[J]. Chinese Journal of Aeronautics, 2015, 28(1):103-111.
[37] 昌皓, 朱芳, 金东海, 等. 叶片掠对跨音转子进口流动的影响[J]. 航空动力学报, 2016, 31(4):857-886. CHANG H, ZHU F, JIN D H, et al. Effect of blade sweep on-inlet flow in transonic compressor rotors[J]. Journal of Aerospace Power, 2016, 31(4):857-886(in Chinese).
[38] WENNERSTROM A J. Design of highly loaded axial-flow fans and compressors[M]. Vermont:Consepts ETI Press, 2000.

Options

Outlines

模态框（Modal）标题

Abstract

Cite this article

References