AIAA JPP Vol 27-6 Nov 2011 - Walker et al - Annular Diffusers with Large Downstream BLockage Effects for Gas Turbine Combustion Applications.AIAA-56386-820.pdf (13.82 MB)
Annular diffusers with large downstream blockage effects for gas turbine combustion applications
journal contributionposted on 2015-10-19, 12:54 authored by Duncan WalkerDuncan Walker, Jon CarrotteJon Carrotte, Paul DenmanPaul Denman
In engineering applications, diffuser performance is significantly affected by its boundary conditions. In a gas turbine combustion system, the space envelope is limited, the inlet conditions are generated by upstream turbomachinery, and the downstream geometry is complex and in close proximity. Published work discusses the impact of compressor-generated inlet conditions, but little work has been undertaken on designing diffusers to accommodate a complex downstream geometry. This paper considers the design of an annular diffuser in the presence of a large downstream blockage. This is most applicable in the combustion system of a low-emission landbased aero-derivative gas turbine, where immediately downstream of the diffuser approximately 85% of the flow moves outboard and 15% moves inboard to supply the various flame-tube and turbine-cooling features. Several diffuser concepts are numerically developed and demonstrate 1) the interaction between the diffuser and downstream geometry and 2) how this varies with changes in diffuser geometry. A preferred concept is experimentally evaluated on a low-speed facility that simulates the combustion system and provides compressorgenerated inlet conditions. A conventionally designed aero-derivative diffuser system is also evaluated and, with reference to this datum, the system total pressure losses are reduced by between 20 and 35%.
- Aeronautical, Automotive, Chemical and Materials Engineering
- Aeronautical and Automotive Engineering
Published inJOURNAL OF PROPULSION AND POWER
Pages1218 - 1230 (13)
CitationWALKER, A.D., CARROTTE, J.F. and DENMAN, P.A., 2011. Annular diffusers with large downstream blockage effects for gas turbine combustion applications. Journal of Propulsion and Power, 27(6), pp. 1218-1230.
Publisher©2011 by the authors. Published by the American Institute of Aeronautics and Astronautics
- VoR (Version of Record)
Publisher statementThis work is made available according to the conditions of the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence. Full details of this licence are available at: https://creativecommons.org/licenses/by-nc-nd/4.0/
NotesThis paper was published in the Journal of Propulsion and Power and the definitive published version is available at http://dx.doi.org/10.2514/1.B34167