Improving the performance of high-speed axial compressors through low-speed model compressor testing has proved to be economical and effective (Wisler, 1985). The key to this technique is to design low-speed blade profiles that are aerodynamically similar to their high-speed counterparts. The conventional aerodynamic similarity transformation involves the small disturbance potential flow assumption; therefore, its application is severely limited and generally not used in practical design. In this paper, a set of higher order transformation rules are presented that can accommodate large disturbances at transonic speed and are therefore applicable to similar transformations between the high-speed high-pressure compressor and its low-speed model. Local linearization is used in the nonlinear equations and the transformation is obtained in an iterative process. The transformation gives the global blading parameters such as camber, incidence, and solidity as well as the blade profile. Both numerical and experimental validations of the transformation show that the nonlinear similarity transformations do retain satisfactory accuracy for highly loaded blades up to low transonic speeds. Further improvement can be made by only slightly modifying profiles numerically without altering the global similarity parameters.
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July 1992
Research Papers
Similarity Transformations for Compressor Blading
N. G. Zhu,
N. G. Zhu
Jet Propulsion Department, Beijing University of Aeronautics and Astronautics, Beijing 100083, People’s Republic of China
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L. Xu,
L. Xu
Jet Propulsion Department, Beijing University of Aeronautics and Astronautics, Beijing 100083, People’s Republic of China
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M. Z. Chen
M. Z. Chen
Jet Propulsion Department, Beijing University of Aeronautics and Astronautics, Beijing 100083, People’s Republic of China
Search for other works by this author on:
N. G. Zhu
Jet Propulsion Department, Beijing University of Aeronautics and Astronautics, Beijing 100083, People’s Republic of China
L. Xu
Jet Propulsion Department, Beijing University of Aeronautics and Astronautics, Beijing 100083, People’s Republic of China
M. Z. Chen
Jet Propulsion Department, Beijing University of Aeronautics and Astronautics, Beijing 100083, People’s Republic of China
J. Turbomach. Jul 1992, 114(3): 561-568 (8 pages)
Published Online: July 1, 1992
Article history
Received:
February 20, 1991
Online:
June 9, 2008
Citation
Zhu, N. G., Xu, L., and Chen, M. Z. (July 1, 1992). "Similarity Transformations for Compressor Blading." ASME. J. Turbomach. July 1992; 114(3): 561–568. https://doi.org/10.1115/1.2929180
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