Off-design performance comparison between single and two-shaft engines: part 1 — fixed geometry

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dc.contributor.authorNikolaidis, Theoklis
dc.contributor.authorPellegrini, Alvise
dc.contributor.authorSaravanamuttoo, H. I. H.
dc.contributor.authorAslanidou, I.
dc.contributor.authorKalfas, A.
dc.contributor.authorPilidis, Pericles
dc.date.accessioned2021-01-28T14:46:58Z
dc.date.available2021-01-28T14:46:58Z
dc.date.issued2021-01-11
dc.description.abstractThis paper describes an investigation into the off-design performance comparison of single and two-shaft gas turbine engines. A question that has been asked for a long time which gas turbine delivers a better thermal efficiency at part load. The authors, notwithstanding their intensive searches, were unable to find a comprehensive answer to this question. A detailed investigation was carried out using a state of the art performance evaluation method and the answer was found to be: It depends! In this work, the performance of two engine configurations is assessed. In the first one, the single-shaft gas turbine operates at constant shaft rotational speed. Thus, the shape of the compressor map rotational speed line will have an important influence on the performance of the engine. To explore the implications of the shape of the speed line, two single-shaft cases are examined. The first case is when the speed line is curved and as the compressor pressure ratio falls, the non-dimensional mass flow increases. The second case is when the speed line is vertical and as the compressor pressure ratio falls, the non-dimensional mass flow remains constant. In the second configuration, the two-shaft engine, the two-shafts can be controlled to operate at different rotational speeds and also varying relationships between the rotational speeds. The part-load operation is characterized by a reduction in the gas generator rotational speed. The tool, which was used in this study, is a 0-D whole engine simulation tool, named Turbomatch. It was developed at Cranfield and it is based on mass and energy balance, carried out through an iterative method, which is based on component maps. These generic, experimentally derived maps are scaled to match the design point of a particular engine before an off-design calculation is performed. The code has been validated against experimental data elsewhere, it has been used extensively for academic purposes and the research activities that have taken place at Cranfield University. For an ideal cycle, the single-shaft engine was found to be a clear winner in terms of part-load thermal efficiency. However, this picture changed when realistic component maps were utilized. The basic cycle and the shape of component maps had a profound influence on the outcome. The authors explored the influence of speed line shapes, levels of component efficiencies and the variation of these component efficiencies within the operating range. This paper describes how each one of these factors, individually, influences the outcome.en_UK
dc.identifier.citationNikolaidis T, Pellegrini A, Saravanamuttoo HIH, et al., (2021) Off-design performance comparison between single and two-shaft engines: part 1 — fixed geometry. In: ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, 21-25 September 2020, London, Virtual Event. GT2020-14500en_UK
dc.identifier.isbn978-0-7918-8419-5
dc.identifier.urihttps://doi.org/10.1115/GT2020-14500
dc.identifier.urihttps://asmedigitalcollection.asme.org/GT/proceedings/GT2020/84195/Virtual,%20Online/1095107
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/16275
dc.language.isoenen_UK
dc.publisherAmerican Society of Mechanical Engineersen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectgas turbine performanceen_UK
dc.subjectsingle-shaften_UK
dc.subjecttwo-shaften_UK
dc.subjectthermal efficiencyen_UK
dc.subjectspecific worken_UK
dc.titleOff-design performance comparison between single and two-shaft engines: part 1 — fixed geometryen_UK
dc.typeConference paperen_UK

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