Assessment of performance boundaries and operability of low specific thrust GUHBPR engines for EIS2025

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dc.contributor.authorMo, Da
dc.contributor.authorRoumeliotis, Ioannis
dc.contributor.authorMourouzidis, Christos
dc.contributor.authorKissoon, Sajal
dc.contributor.authorLiu, Yixiong
dc.date.accessioned2022-05-04T11:33:31Z
dc.date.available2022-05-04T11:33:31Z
dc.date.issued2022-04-25
dc.description.abstractThis paper aims to develop a robust design process by approaching the performance boundaries and evaluating the operability of the pursued geared turbofan engine with low specific thrust for EIS 2025. A two-spool direct-drive turbofan (DDTF) engine of EIS 2000 was improved according to aircraft specifications and technology boundaries in 2025. A series of optimized engines with consecutive fan diameters were established to seek the ideal engine by balancing SFC, weight and mission fuel burn. The fan diameter was proved to be a decisive factor for lowering SFC and energy usage. The cycle design optimization process achieved a thermal efficiency of approximately 52%, and a propulsive efficiency of 79.5%, which is 8.19% increase in propulsive efficiency by enlarging fan diameter from 1.6m to 1.9m. Meanwhile, the 1.9m-fan diameter engine achieved a reduction in SFC and fuel burn of 7.47% and 6.58% respectively which offers an overall reduction of 30.82% in block fuel burnt and CO2 emission compared to the DDTF engine. A feasibility check verified the viability of the designed optimum engine in terms of fan tip speed, stage loading and AN2. Dynamic simulation offered a deep understanding of transient behaviour and fundamental mechanism of the geared turbofan engine. An important aspect of this paper is the use of advanced CMC materials, which led to an improvement of 4.92% in block fuel burn and 2.93% in engine weight.en_UK
dc.identifier.citationMo D, Roumeliotis I, Mourouzidis C, et al., (2022) Assessment of performance boundaries and operability of low specific thrust GUHBPR engines for EIS2025. Journal of Engineering for Gas Turbines and Power, Volume 144, Issue 7, July 2022, Paper number GTP-21-1595en_UK
dc.identifier.issn0742-4795
dc.identifier.urihttps://doi.org/10.1115/1.4054405
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/17859
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.titleAssessment of performance boundaries and operability of low specific thrust GUHBPR engines for EIS2025en_UK
dc.typeArticleen_UK

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