Aeroengine transient performance simulation integrated with generic heat soakage and tip clearance model

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dc.contributor.authorLi, Zhuojun
dc.contributor.authorLi, Yi-Guang
dc.contributor.authorSampath, Suresh
dc.date.accessioned2022-05-30T18:31:14Z
dc.date.available2022-05-30T18:31:14Z
dc.date.issued2022-03-11
dc.description.abstractThe simulations and assessment of transient performance of gas turbine engines during the conceptual and preliminary design stage may be conducted ignoring heat soakage and tip clearance variations due to lack of detailed geometrical and structural information. As a result, problems with transient performance stability may not be revealed correctly, and corresponding design iterations would be necessary and costly when those problems are revealed at a detailed design stage. To make an engine design more cost and time effective, it has become important to require better transient performance simulations during the conceptual and preliminary design stage considering all key impact factors such as fuel control schedule, rotor dynamics, inter-component volume effect as well as heat soakage and tip clearance variation effects. In this research, a novel transient performance simulation approach with generically simplified heat soakage and tip clearance models for major gas path components of gas turbine engines including compressors, turbines and combustors has been developed to support more realistic transient performance simulations of gas turbine engines at conceptual and preliminary design stages. Such heat soakage and tip clearance models only require thermodynamic design parameters as input, which is normally available during such design stages. The models have been implemented into in-house transient performance simulation software and applied to a model twin-spool turbojet engine to test their effectiveness. Comparisons between transient performance simulated with and without the heat soakage and tip clearance effects demonstrate that the results are promising. Although the introduced heat soakage and tip clearance models may not be as accurate as that using detailed component geometrical information, it is able to include the major heat soakage and tip clearance effects and make the transient performance simulations and analysis more realistic during conceptual and preliminary engine design stage.en_UK
dc.identifier.citationLi Z, Li Y-G, Sampath S. (2022) Aeroengine transient performance simulation integrated with generic heat soakage and tip clearance model. The Aeronautical Journal, Volume 126, Issue 1302, August 2022, pp. 1265-1287en_UK
dc.identifier.issn0001-9240
dc.identifier.urihttps://doi.org/10.1017/aer.2022.15
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/17974
dc.language.isoenen_UK
dc.publisherCambridge University Pressen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectheat soakageen_UK
dc.subjecttip clearanceen_UK
dc.subjecttransient performanceen_UK
dc.subjectthermodynamic performance simulationen_UK
dc.subjectgas turbine engineen_UK
dc.titleAeroengine transient performance simulation integrated with generic heat soakage and tip clearance modelen_UK
dc.typeArticleen_UK

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