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Detailed Measurements on a Modern Combustor Dump Diffuser System PUBLIC ACCESS

[+] Author Affiliations
J. F. Carrotte, D. W. Bailey

Loughborough University, Loughborough, Leics, UK

C. W. Frodsham

Rolls Royce plc, Bristol, UK

Paper No. 94-GT-299, pp. V003T06A023; 8 pages
doi:10.1115/94-GT-299
From:
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7885-9
  • Copyright © 1994 by ASME

abstract

An experimental investigation has been carried out to determine the flow characteristics and aerodynamic performance of a modern gas turbine combustor dump diffuser. The system comprised of a straight walled pre-diffuser, of area ratio 1.35, which projected into a dump cavity where the flow divided to pass either into the flame tube or surrounding feed annuli. In addition, a limited amount of air was removed to simulate flow used for turbine cooling. The flame tube was relatively deep, having a radial depth 5.5 times that of the passage height at pre-diffuser inlet, and incorporated burner feed arms, cowl head porosity, cooling rings and primary ports. Representative inlet conditions to the diffuser system were generated by a single stage axial flow compressor.

Results are presented for the datum configuration, and for a further three geometries in which the distance between pre-diffuser exit and the head of the flame tube (ie. dump gap) was reduced. Relatively high values of stagnation pressure loss were indicated, with further significant increases occurring at smaller dump gaps. These high losses, which suggest a correlation with other published data, are due to the relatively deep flame tube and short diffuser length. Furthermore, the results also focus attention on how the presence of a small degree of diffuser inlet swirl, typical of that which may be found within a gas turbine engine, can result in large swirl angles being generated further downstream around the flame tube. This is particularly true for flow passing to the inner annulus.

Copyright © 1994 by ASME
This article is only available in the PDF format.

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