Abstract
The object of this paper is to provide a reliable tool to carry out the parametrical studies of post-stall behaviors in multistage axial compression systems. An adapted version of the 1.5D Euler equations with additional source terms is discretized with a finite volume method and are solved in time by a fourth-order Runge–Kutta scheme. The equations are discretized at mid-span both inside the blade rows and the non-bladed regions. The source terms express the blade-flow interactions and are estimated by calculating the velocity triangles for each blade row. Additional source terms are introduced to represent the effects of inlet disturbances on post-stall behaviors and the physical analysis is therefore proposed to explain the phenomenon.
Article PDF
Similar content being viewed by others
Avoid common mistakes on your manuscript.
References
Adam, O. and Léonard, O., A Quasi-One-Dimensional Model for Axial Compressor, 17th ISABE Conf., 2005.
Léonard, O. and Adam, O., A Quasi-One-Dimensional Model for Multistage Turbomachinery, J. Therm. Sci., 2008, vol. 17, no. 1, pp. 7–20.
Wenhai, Du. and Léonard, O., A Quasi-One-Dimensional CFDModel forMultistage Compressors, ASME, pap. GT-2011-45497.
Wenhai, Du. and Léonard, O., Numerical Simulation of Surge in Axial Compressor, Int. J. Rot. Machin., 2012, article ID 164831.
Du, W., Jun Qiang, Zh., and Léonard, O., Dynamic Simulations of Post-Stall Performance in Multistage Axial Compressors, J. Therm. Sci., 2012, vol. 21, no. 4, pp. 1–11.
Crawford, R.A. and Burwell, A.E., Quantitative Evaluation of Transient Heat Transfer on Axial Flow Compressor Stability, AIAA/SAE/ASME/ASEE, 21st Joint Propulsion Conf., AIAA,Monterey, CA, 1985, pap. 85–1352.
Leinhos, D.C., Schmid, N.R., and Fottner, L., The Influence of Transient Inlet Distortions on the Instability Inception of a Low-Pressure Compressor in a Turbofan Engine, J. Turbomach., 2000, vol. 123, no. 1, pp. 1–8.
Lin, F., Li, M., and Chen, J., Long-to-Short Length-Scale Transition: A Stall Inception Phenomenon in an Axial Compressor with Inlet Distortion, J. Turbomach., 2005, vol. 128, no. 1, pp. 130–140.
Davis, M.W., A Stage-by-Stage Post-Stall Compression System Modeling Technique: Methodology, Validation, and Application, PhD Thesis, Virginia Polytechnic Institute and State University, 1987.
Tauveron, N., Saez, M., Ferrand, P., and Leboeuf, F., Axial TurbomachineModeling with a 1D Axisymmetric Approach. Application to Gas Cooled Nuclear Reactor, Nucl. Eng. Des., 2007, vol. 237, pp. 1679–1692.
Tauveron, N., Simulation Numérique et Analyse du Déclenchement et du Développement des Instabilités Axiales dans les Turbomachines. Application àun Transitoire de Brèche dans un Réacteur Nucléaire àHélium, PhD Thesis, Ecole Centrale de Lyon, 2006.
Day, I.J., Axial Compressor Performance during Surge, J. Propuls. Power, 1994, vol. 10, no. 3, pp. 329–336.
Gamache, R.N. and Greitzer, E.M., Reverse Flow inMultistage AxialCompressors, J. Propuls. Power, 1990, vol. 6, no. 4, pp. 461–473.
Greitzer, E.M., Surge and Rotating Stall in Axial Flow Compressors, Part I: Theoretical Compression System Model, J. Eng. Power, 1976, vol. 98, no. 2, pp. 190–198.
Greitzer, E.M., Surge and Rotating Stall in Axial Flow Compressors, Part II: Experimental Results and Comparison with Theory, J. Eng. Power, 1976, vol. 98, no. 2, pp. 199–211.
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
About this article
Cite this article
Du, W., Yunfeng, X. & Lorenzini, G. The Influence of Inlet Disturbances on the Post-Stall Behaviors in Compression System. J. Engin. Thermophys. 27, 58–71 (2018). https://doi.org/10.1134/S1810232818010071
Received:
Published:
Issue Date:
DOI: https://doi.org/10.1134/S1810232818010071