The off-design performance prediction of axial compressor based on a 2D approach

• Autorzy: Zhu X. C. , Hu J. F. , Ou-Yang H. , Tian J. , Qiang X. Q. , Du Z. H.
• Języki publikacji: EN

Abstrakty

EN

The two-dimensional compressor flow simulation approach has always been a very valuable tool in compressor preliminary design studies, as well as performance predictions. In this context, a general development of the streamline curvature (SLC) method is elucidated firstly. Then a numerical method based on SLC is developed to simulate the internal flow of the compressor according to the development analysis and conclusion. Two certain transonic axial compressors are calculated by this 2D method. The speed lines and span-wise aerodynamic parameters are compared with the experiment data in order to demonstrate the method presented in this paper.

Słowa kluczowe

EN

two-dimensional; compressor; streamline curvature; deviation; loss model

• Wydawca: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
• Czasopismo: Journal of Theoretical and Applied Mechanics
• Rocznik: 2013
• Tom: Vol. 51 nr 3
• Strony: 523--531
• Opis fizyczny: Bibliogr. 22 poz., rys.

Twórcy

autor

Zhu X. C.

• Shanghai JiaoTong University, School of Mechanical Engineering, Shanghai, China

autor

Hu J. F.

• Shanghai JiaoTong University, School of Mechanical Engineering, Shanghai, China

autor

Ou-Yang H.

• Shanghai JiaoTong University, School of Mechanical Engineering, Shanghai, China

autor

Tian J.

• Shanghai JiaoTong University, School of Mechanical Engineering, Shanghai, China

autor

Qiang X. Q.

• Shanghai JiaoTong University, School of Mechanical Engineering, Shanghai, China

autor

Du Z. H.

• Shanghai JiaoTong University, School of Mechanical Engineering, Shanghai, China

Bibliografia

• 1. Arima T.A., 1999, Numerical investigation of transonic axial compressor rotor flow using a low--Reynolds-number k − ε turbulence model, Journal of Turbomachinery, 121, 44-58
• 2. Aungier R.H., 2003, Axial-Flow Compressor: A Strategy for Aerodynamic Design and Analysis, ASME Press, New York
• 3. Bloch G.S., Copenhaver W.W., O’Brien W.F., 1999, A shock loss model for supersonic compressor cascades, ASME Journal of Turbomachinery, 121, 28-35
• 4. Boyer K.M., 2003, An improved streamline curvature approach for off-design analysis of transonic axial compression systems, ASME Journal of Turbomachinery, 125, 475-481
• 5. Cetin M., Ucer A.S., Hirsch C., Serovy G.K., 1987, Application of modified loss and deviation correlations to transonic axial compressors, AGRAD Report, paper AGRAD-R-745
• 6. Creveling H.F., Carmody R.H., 1968, Axial-flow compressor computer program for calculating off-design performance, NASA-CR-72472
• 7. Denton J.D., Dawes W.N., 1999, Computational fluid dynamics for turbomachinery design, Proceedings of the Institution of Mechanical Engineers, Journal of Mechanical Engineering Science, 213, C2
• 8. Hearsey R.M., 1994, Program HT0300 NASA 1994 Version, The Boeing Company, paper D6-81569TN
• 9. Johnsen I.A., Bullock R.O., 1965, Aerodynamic Design of Axial-Flow Compressors, NASA
• 10. Koch C.C., Smith L.H., 1976, Loss sources and magnitudes in axial-flow compressors, ASME Journal of Engineering for Power, 98, 411-424
• 11. König W.M, Henneck D.K., Fottner L., 1994a, Improved blade profile loss and deviation angle models for advanced transonic compressor bladings: Part I: A model for subsonic flow, Journal of Turbomachinery, 117, 81-87
• 12. König W.M, Henneck D.K., Fottner L., 1974b, Improved blade profile loss and deviation angle models for advanced transonic compressor bladings: Part II: A model for supersonic flow, Journal of Turbomachinery, 118, 73-80
• 13. Lieblein S., 1957, Analysis of experimental low-speed loss and stall characteristics of two-dimensional compressor blade cascades, NASA Research Memorandum, paper NACA-RM-E57A28
• 14. Lieblein S., 1959, Loss and stall analysis of compressor cascades, Journal of Basic Engineering, 81, 387-400
• 15. Lieblein S., Roudebush W.H., 1956, Theoretical loss relations for low-speed two dimensional-cascade flow, NASA Technical Note, paper NACA-TN-3662
• 16. Milan V.P., Alexander W., Milan B.B., 2009, Development and validation of a new universal through flow method for axial compressors, Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air, Orlando, Florida, USA, Paper GT 2009-59938
• 17. Miller G.R., Lewis G.W., Hartmann M.J., 1961, Shock losses in transonic rotor rows, ASME Journal of Engineering for Power, 83, 235-242
• 18. Pachidis V., Pilidis P., Templalexis I., Alexander T., Kotsiopoulos P., 2006, Prediction of engine performance under compressor inlet flow distortion using streamline curvature, Proceedings ASME Turbo Expo, Power For Land, Sea and Air, Barcelona, Spain, Paper GT2006-90806
• 19. Royce D.M., Lonnie R., 1980, Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05, NASA Paper, paper NASA-TP-1659
• 20. Schwenk F.C., Lewis G.W., Hartman M.J., 1957, A preliminary analysis of the magnitude of shock losses in transonic compressors, NACA RM E57A30
• 21. Swan W.C., 1961, A practical method of predicting transonic compressor performance, ASME Journal of Engineering for Power, 86, 322-330
• 22. Templalexis I., Pilidis P., Pachidis V., Kotsiopoulos P., 2006, Development of a 2D compressor streamline curvature code, Proc. ASME Turbo Expo, Power For Land, Sea and Air, Barcelona, Spain, Paper GT2006-90867