Numerical study of stall inception in a transonic axial compressor rotor based on the throttle model

• Autorzy: Zhu X. , Liu B. , Hu J. , Shen X.

Identyfikatory

DOI

10.15632/jtam-pl.53.2.307

• Języki publikacji: EN

Abstrakty

EN

The goal of the current paper is to investigate inner flow behavior on stall inception in a transonic compressor rotor. The stall inception process is numerically carried out by unsteady 3-D simulations based on the throttle model. The current study shows that stall starts from the tip of the blade, and stall cell extends to the axial, circumferential and radial directions. Through the comparison of flow transition characteristics at different flow rate conditions, the interface between the incoming flow and tip clearance flow shifts forward to the upstream as the mass flow decreases. Eventually, the shock detaches from the blade leading edge, and tip clearance flow spills into the adjacent blade passage, thus stall happens in the affected blade passages.

Słowa kluczowe

EN

stall; axial compressor; throttle; tip clearance flow

• Wydawca: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
• Czasopismo: Journal of Theoretical and Applied Mechanics
• Rocznik: 2015
• Tom: Vol. 53 nr 2
• Strony: 307--316
• Opis fizyczny: Bibliogr. 17 poz., rys.

Twórcy

autor

Zhu X.

• School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai, China

autor

Liu B.

• School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai, China

autor

Hu J.

• School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai, China

autor

Shen X.

• School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai, China

Bibliografia

• 1. Chen J.-P., Hathaway M.D., Herrick G.P., 2008, Prestall behavior of a transonic axial compressor stage via time-accurate numerical simulation, Journal of Turbomachinery, 130, 4, 041014
• 2. Cumpsty N.A., 1989, Compressor Aerodynamics, Longman Scientific & Technical, London
• 3. Davis R.L., Yao J., 2006, Axial compressor rotor flow structure at stall-inception, 44th AIAA Aerospace Sciences Meeting and Exhibition, 9-12 January, Reno, Nevada
• 4. Day I., 1993, Stall inception in axial flow compressors, Journal of Turbomachinery, 115, 1, 1-9
• 5. Emmons H.W., Pearson C.E., Grant H.P., 1955, Compressor surge and stall propagation, Journal of Turbomachinery, Transactions of the ASME, 77, 455-467
• 6. Furukawa M., Saiki K., Yamada K., Inoue M., 2000, Unsteady flow behavior due to breakdown of tip vortex in an axial compressor rotor at near-stall condition, ASME-TURBO-EXPO, Munich, Germany
• 7. Hah C., Bergner J.R., Schiffer H.-P., 2006, Short length-scale rotating stall inception in a transonic axial compressor: criteria and mechanisms, ASME Turbo Expo 2006: Power for Land, Sea, and Air, Barcelona, Spain
• 8. Hah C., Rabe D.C., Wadia A.R., 2004, Role of tip-leakage vortices and passage shock in stall inception in a swept transonic compressor rotor, ASME Turbo Expo 2004: Power for Land, Sea, and Air, Vienna, Austria
• 9. Hah C., Schulze R., Wagner S., Hennecke D.K., 1999, Numerical and experimental study for short wavelength stall inception in a low-speed axial compressor, Proceedings of 14th International Symposium Air Breathing Engines, Florence, Italy
• 10. He L., 1997, Computational study of rotating-stall inception in axial compressors, Journal of Propulsion and Power, 13, 1, 31-38
• 11. Hoying D.A., Tan C.S., Greitzer E., Vo H.D., 1999, Role of blade passage flow structures in axial compressor rotating stall inception, Journal of Turbomachinery, 121, 4, 735-742
• 12. Hu J.F., Zhu X.C., Ou-Yang H., Tian J., Wu Y.D., Qiang X.Q., Zhao G., Du Z.H., 2013, The unsteadiness of tip clearance flow and its effect to stability of transonic axial compressor, Journal of Theoretical and Applied Mechanics, 51, 2, 431-438
• 13. Moore F., Greitzer E., 1986, A theory of post-stall transients in axial compression systems: Part I – Development of equations, Journal of Engineering for Gas Turbines and Power, 108, 1, 68-76
• 14. Niazi S., 2000, Numerical simulation of rotating stall and surge alleviation in axial compressors, Ph.D. Thesis, Georgia Institute of Technology
• 15. Vo H.D., Tan C.S., Greitzer E.M., 2008, Criteria for spike initiated rotating stall, Journal of Turbomachinery, 130, 1, 011023
• 16. Yamada K., Funazaki K., Furukawa M., 2007, The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor, ASME Turbo Expo 2007: Power for Land, Sea, and Air, Montreal, Canada
• 17. Yao J., Cargill P.L., Holmes D.G., Gorrell S.E., 2010, Aspects of numerical analysis for unsteady flows in aircraft engines, 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida