Title
Effect of inlet swirl on the performance of annular diffusers having the same equivalent cone angle
Abbreviated Journal Title
Proc. Inst. Mech. Eng. Part G-J. Aerosp. Eng.
Keywords
annular diffuser; gas turbine engine; equivalent cone angle; inlet; swirl; static pressure recovery coefficient; total pressure loss; coefficient; COMPRESSOR EXIT CONDITIONS; COMBUSTOR; FLOW; Engineering, Aerospace; Engineering, Mechanical
Abstract
Annular diffusers are an integral component of the gas turbine engines of high-speed aircraft. These facilitate effective operation of the combustor by reducing the total pressure loss. The performance characteristics of these diffusers depend on their geometry and the inlet conditions. The present investigation attempts to select the range of the inlet swirl intensity for the best performance of annular diffusers with different geometries but having the same equivalent cone angle. This is analysed on the basis of the static pressure recovery and total pressure loss coefficients. The results show that the parallel diverging hub and casing annular diffuser produces the best performance at high-swirl intensities.
Journal Title
Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering
Volume
220
Issue/Number
G2
Publication Date
1-1-2006
Document Type
Article
Language
English
First Page
129
Last Page
143
WOS Identifier
ISSN
0954-4100
Recommended Citation
"Effect of inlet swirl on the performance of annular diffusers having the same equivalent cone angle" (2006). Faculty Bibliography 2000s. 6592.
https://stars.library.ucf.edu/facultybib2000/6592
Comments
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