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Numerical investigation of dump diffuser combustor performance at uniform and non-uniform inlet conditions

Wang, H; Luo, KH; (2020) Numerical investigation of dump diffuser combustor performance at uniform and non-uniform inlet conditions. In: Proceedings of ASME Turbo Expo 2020. ASME: Virtual, Online.

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Abstract

A numerical investigation has been conducted for an axisymmetric dump diffuser combustor, which is a simplified geometry of a typical lean-burn combustor in a modern civil aero-engine gas turbine. The aerodynamic performance of the combustor is analyzed with an emphasis on two common performance parameters: static pressure recovery and total pressure loss. The former is essential in maintaining high-pressure air flow across the liner, whereas the latter involves the specific fuel consumption of the aero-engine. At first, the effects of geometrical parameters of the dump diffuser combustor are investigated. A high diffuser angle seems to be detrimental to both static pressure recovery and total pressure loss. On the other hand, a high dump gap ratio is beneficial from the aerodynamic performance point of view. However, all these desired characteristics are subject to mechanical constraints and their implications for specific consumption. Optimum values of those parameters should exist for a given desired aerodynamics performance. The majority of previous researches, including the first part of this study, have been carried out with uniform inlet conditions due to a typical independent design cycle of each component. The effects of compressor exit conditions are usually not considered in the early stage design process. In the second part of this study, various inlet conditions representing a more realistic compressor exit condition such as inlet symmetrical and asymmetrical boundary layer thickness are investigated. The performance of an asymmetrical configuration with a thin boundary layer thickness near the outer annulus is almost comparable to that of its uniform counterpart. Findings of this study provide useful input for combustor designers to improve the combustor’s performance based on the compressor exit conditions.

Type: Proceedings paper
Title: Numerical investigation of dump diffuser combustor performance at uniform and non-uniform inlet conditions
Event: Turbomachinery Technical Conference and Exposition GT2020
ISBN-13: 9780791884133
DOI: 10.1115/GT2020-15982
Publisher version: https://doi.org/10.1115/GT2020-15982
Language: English
Additional information: © 2020 American Society of Mechanical Engineers (ASME). All rights reserved. This version is the version of record. For information on re-use, please refer to the publisher’s terms and conditions.
Keywords: Combustion chambers, Diffusers, Pressure, Compressors, Aircraft engines, Boundary layers, Design, Aerodynamics, Air flow, Annulus, Cycles, Degrees of freedom, Fuel consumption, Gas turbines, Geometry, High pressure (Physics), Symmetry (Physics)
UCL classification: UCL
UCL > Provost and Vice Provost Offices
UCL > Provost and Vice Provost Offices > UCL BEAMS
UCL > Provost and Vice Provost Offices > UCL BEAMS > Faculty of Engineering Science
UCL > Provost and Vice Provost Offices > UCL BEAMS > Faculty of Engineering Science > Dept of Mechanical Engineering
URI: https://discovery.ucl.ac.uk/id/eprint/10120850
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