Design optimisation of separate-jet exhausts for the next generation of civil aero-engines

Simple item page
dc.contributor.authorGoulos, Ioannis
dc.contributor.authorOtter, John J.
dc.contributor.authorStankowski, Tomasz
dc.contributor.authorMacManus, David G.
dc.contributor.authorGrech, Nicholas
dc.contributor.authorSheaf, Christopher
dc.date.accessioned2017-09-29T15:28:04Z
dc.date.available2017-09-29T15:28:04Z
dc.date.issued2017-09-08
dc.description.abstractThis paper presents the development and application of a computational framework for the aerodynamic design of separate-jet exhaust systems for Very-High-Bypass-Ratio (VHBR) gas-turbine aero-engines. An analytical approach is synthesised comprising a series of fundamental modelling methods. These address the aspects of engine performance simulation, parametric geometry definition, viscous/compressible flow solution, design space exploration, and genetic optimisation. Parametric design is carried out based on minimal user-input combined with the cycle data established using a zero-dimensional (0D) engine analysis method. A mathematical approach is developed based on Class-Shape Transformation (CST) functions for the parametric geometry definition of gas-turbine exhaust components such as annular ducts, nozzles, after-bodies, and plugs. This proposed geometry formulation is coupled with an automated mesh generation approach and a Reynolds Averaged Navier–Stokes (RANS) flow-field solution method, thus forming an integrated aerodynamic design tool. A cost-e ective Design Space Exploration (DSE) and optimisation strategy has been structured comprising methods for Design of Experiment (DOE), Response Surface Modelling (RSM), as well as genetic optimisation. The integrated framework has been deployed to optimise the aerodynamic performance of a separate-jet exhaust system for a large civil turbofan engine representative of future architectures. The optimisations carried out suggest the potential to increase the engine’s net propulsive force compared to a baseline architecture, through optimum re-design of the exhaust system. Furthermore, the developed approach is shown to be able to identify and alleviate adverse flow-features that may deteriorate the aerodynamic behaviour of the exhaust system.en_UK
dc.identifier.citationGoulos I, Otter J, Stankowski T, et al., (2017) Design optimisation of separate-jet exhausts for the next generation of civil aero-engines. Proceedings of 23rd International Symposium for Air-Breathing Engines - ISABE 2017, 4-8 September 2017, Manchester, UKen_UK
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/12564
dc.language.isoenen_UK
dc.publisherISABEen_UK
dc.rights©2017 The Authors. This is the Author Accepted Manuscript. The Authors retain copyright.
dc.subjectGas turbinesen_UK
dc.subjectTurbofanen_UK
dc.subjectExhaust nozzlesen_UK
dc.subjectAerodynamicsen_UK
dc.subjectComputational fluid dynamicsen_UK
dc.subjectDesign optimisationen_UK
dc.subjectClass-shape transformation functionsen_UK
dc.titleDesign optimisation of separate-jet exhausts for the next generation of civil aero-enginesen_UK
dc.typeConference paperen_UK

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
Design_optimisation_of_separate-jet_exhausts-2017.pdf
Size:
1.88 MB
Format:
Adobe Portable Document Format
Download
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.79 KB
Format:
Item-specific license agreed upon to submission
Description:
Download

Collections

Staff publications (SATM)