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Author Okelah, M. R. S.en_US
Available date 2009-11-25T13:06:11Zen_US
Publication Date 1988en_US
Publication Name Engineering Journal of Qatar University
Citation Engineering Journal of Qatar University, 1988, Vol. 1, Pages 143-162.en_US
URI http://hdl.handle.net/10576/7969en_US
Abstract The concept of co-rotating axial compressor was conceived primarily as a means of overcoming the inherent rotational speed mismatch between a fan and its driving turbine in moderate to high bypass ratio turbo-fan engines. In essence, the arrangement serves as a torque converter or "aerodynamic gear box" transferring a fraction of the energy supplied by the high pressure turbine to the compressor casing shaft via the co-rotating casing. Thus, considerable modifications in performance of gas turbine engines can be achieved. The present work examines the potential of exploiting the co-rotating compressor concept in major applications of gas turbines, among which are; turbo-fan, turbo-jet, turbo-propeller, turbo-shaft and basic industrial gas turbine engines. The paper formulates torque and power constraints for engines which show feasibility of utilizing a co-rotating compressor. It also formulates speed relationships of components. Basic analyses are carried out, critical parameters are indicated, and characteristics of performance of engine components are discussed, with due consideration of the likelihood of load variationen_US
Language enen_US
Publisher Qatar Universityen_US
Subject Energyen_US
Title The Potential of The Co-Rotating Compressor in Gas Turbine Applicationsen_US
Type Articleen_US
Pagination 143-162en_US
Volume Number 1en_US


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