A new method to solve the transonic flow past a plane cascade with inlet bow wave and a passage shock extending from the leading edge all the way across the flow channel is presented. In this method, different algorithms are used for supersonic and subsonic flow regions, respectively, and the aerothermodynamic relations of a connecting passage shock are satisfied. Within the supersonic region, the method of characteristics is used. For calculation of the subsonic flow, the stream function equation expressed with respect to nonorthogonal curvilinear coordinates and nonorthogonal velocity components is solved with a matrix method. By the use of Rankine-Hugoniot relations, the passage shock can be accurately determined and a definite jump of the aerothermodynamic quantities across the passage shock is obtained. All calculations involved are programmed and incorporated into a single code. The computational procedure is straightforward and simple, and the computational time is short. Some results of typical applications of this method are given in this paper. Agreement of the numerical results with the experimental data, including the location and shape of the passage shock wave, is very good.
Skip Nav Destination
Article navigation
April 1985
Research Papers
Transonic Cascade Flow Solved by Separate Supersonic and Subsonic Computations With Shock Fitting
Wenquan Wu,
Wenquan Wu
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China
Search for other works by this author on:
Chung-Hua Wu,
Chung-Hua Wu
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China
Search for other works by this author on:
Dabang Yu
Dabang Yu
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China
Search for other works by this author on:
Wenquan Wu
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China
Chung-Hua Wu
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China
Dabang Yu
Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China
J. Eng. Gas Turbines Power. Apr 1985, 107(2): 329-335 (7 pages)
Published Online: April 1, 1985
Article history
Received:
December 19, 1983
Online:
October 15, 2009
Article
Article discussed|
View article
Citation
Wu, W., Wu, C., and Yu, D. (April 1, 1985). "Transonic Cascade Flow Solved by Separate Supersonic and Subsonic Computations With Shock Fitting." ASME. J. Eng. Gas Turbines Power. April 1985; 107(2): 329–335. https://doi.org/10.1115/1.3239723
Download citation file:
Get Email Alerts
Cited By
Assessment of a Liquid Hydrogen Conditioning System for Retrofitting on Kerosene Designed Turbofans
J. Eng. Gas Turbines Power
Characterization of Crankcase Ventilation Gas on Stationary Natural Gas Engines
J. Eng. Gas Turbines Power
DGEN Aeropropulsion Research Turbofan Core/Combustor-Noise Measurements—Source Separation
J. Eng. Gas Turbines Power
Related Articles
A Numerical Method for Turbomachinery Aeroelasticity
J. Turbomach (April,2004)
Influence of Deposit on the Flow in a Turbine Cascade
J. Turbomach (October,1988)
Related Chapters
To-Be-Recorded Analysis inside Derivative Code Compiler
International Conference on Software Technology and Engineering, 3rd (ICSTE 2011)
Scalability of Abinit on BlueGene/L for Identifying the Band Structure for Nanotechnology Materials
International Conference on Advanced Computer Theory and Engineering (ICACTE 2009)
Covariance Regularization for Supervised Learning in High Dimensions
Intelligent Engineering Systems through Artificial Neural Networks, Volume 20