Aerodynamic design of separate-jet exhausts for future civil aero engines, Part I: parametric geometry definition and CFD approach

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dc.contributor.authorGoulos, Ioannis
dc.contributor.authorStankowski, Tomasz
dc.contributor.authorOtter, John
dc.contributor.authorMacManus, David G.
dc.contributor.authorGrech, Nicholas
dc.contributor.authorSheaf, Christopher T.
dc.date.accessioned2021-06-11T15:29:33Z
dc.date.available2021-06-11T15:29:33Z
dc.date.issued2016-03-15
dc.description.abstractThis paper presents the development of an integrated approach which targets the aerodynamic design of separate-jet exhaust systems for future gas-turbine aero-engines. The proposed framework comprises a series of fundamental modeling theories which are applicable to engine performance simulation, parametric geometry definition, viscous/compressible flow solution, and Design Space Exploration (DSE). A mathematical method has been developed based on Class-Shape Transformation (CST) functions for the geometric design of axi-symmetric engines with separate-jet exhausts. Design is carried out based on a set of standard nozzle design parameters along with the flow capacities established from zero-dimensional (0D) cycle analysis. The developed approach has been coupled with an automatic mesh generation and a Reynolds Averaged Navier-Stokes (RANS) flow-field solution method, thus forming a complete aerodynamic design tool for separate-jet exhaust systems. The employed aerodynamic method has initially been validated against experimental measurements conducted on a small-scale Turbine Powered Simulator (TPS) nacelle. The developed tool has been subsequently coupled with a comprehensive DSE method based on Latin- Hypercube Sampling (LHS). The overall framework has been deployed to investigate the design space of two civil aero-engines with separate jet exhausts, representative of current and future architectures, respectively. The inter-relationship between the exhaust systems' thrust and discharge coefficients has been thoroughly quantified. The dominant design variables that affect the aerodynamic performance of both investigated exhaust systems have been determined. A comparative evaluation has been carried out between the optimum exhaust design sub-domains established for each engine. The proposed method enables the aerodynamic design of separate-jet exhaust systems for a designated engine cycle, using only a limited set of intuitive design variables. Furthermore, it enables the quantification and correlation of the aerodynamic behavior of separate-jet exhaust systems for designated civil aero-engine architectures. Therefore, it constitutes an enabling technology towards the identification of the fundamental aerodynamic mechanisms that govern the exhaust system performance for a user-specified engine cycleen_UK
dc.identifier.citationGoulos I, Stankowski T, Otter J, et al., (2016) Aerodynamic design of separate-jet exhausts for future civil aero engines, Part I: parametric geometry definition and CFD approach. Journal of Engineering for Gas Turbines and Power, Volume138, Issue 8, August 2016, Article number 081201. Paper number GTP-15-1538en_UK
dc.identifier.issn0742-4795
dc.identifier.urihttps://doi.org/10.1115/1.4032649
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/16759
dc.language.isoenen_UK
dc.publisherASMEen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectseparate-jet exhaust systemsen_UK
dc.subjectgas-turbine aero-enginesen_UK
dc.titleAerodynamic design of separate-jet exhausts for future civil aero engines, Part I: parametric geometry definition and CFD approachen_UK
dc.typeArticleen_UK

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