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AuthorOkelah, M. R. S.
Available date2009-11-25T13:06:11Z
Publication Date1988
Publication NameEngineering Journal of Qatar University
CitationEngineering Journal of Qatar University, 1988, Vol. 1, Pages 143-162.
URIhttp://hdl.handle.net/10576/7969
AbstractThe 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 variation
Languageen
PublisherQatar University
SubjectEnergy
TitleThe Potential of The Co-Rotating Compressor in Gas Turbine Applications
TypeArticle
Pagination143-162
Volume Number1


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