Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Compressor/Diffuser/Combustor Aerodynamic Interactions in Lean Module Combustors

[+] Author and Article Information
A. Duncan Walker, Jon F. Carrotte

Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough LE11 3TU, UK

James J. McGuirk

Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough LE11 3TU, UKj.j.mcguirk@lboro.ac.uk

J. Eng. Gas Turbines Power 130(1), 011504 (Jan 09, 2008) (8 pages) doi:10.1115/1.2747646 History: Received May 01, 2007; Revised May 04, 2007; Published January 09, 2008

The paper reports an experimental investigation into the possibility of increased interactions between combustor external aerodynamics and upstream components, e.g., prediffuser, compressor outlet guide vane (OGV), and even the compressor rotor, caused by the trend in lean module fuel injectors to larger mass flows entering the combustor cowl. To explore these component interaction effects, measurements were made on a fully annular rig comprising a single stage compressor, an advanced integrated OGV/prediffuser, followed by a dump diffuser and a generic combustor flametube with metered cowl and inner/outer annulus flows. The flow split entering the cowl was increased from 30% to 70%. The results demonstrate that, with fixed geometry, as the injector flow increases, the performance of the prediffuser and feed annuli suffer. Prediffuser losses increase and at high injector flow rates, the diffuser moves close to separation. The substantial circumferential variation in cowl flow can feed upstream and cause rotor forcing. Notable differences in performance were observed inline and between injectors at the OGV exit, suggesting that geometry changes such as an increased dump gap or nonaxisymmetric prediffuser designs may be beneficial.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 2

Measurement planes

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Figure 4

Cowl inlet data: minj=50% (top), minj=70% (bottom) (height=80mm, sector angle Δθ=9deg (4-OGV passages))

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Figure 5

Rig inlet axial velocity profile (X1)

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Figure 6

Pitch averaged profiles at rotor exit (X2)

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Figure 7

Rotor exit (X2) static pressure

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Figure 8

OGV exit (reference) total pressure

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Figure 9

Axial velocity contours at OGV exit (X3): (a) 50% between, (b) 70% between, (c) 50% inline, (d) 70% inline (height=36.6mm, sector angle Δθ=4.5deg (2-OGV passages))

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Figure 10

Axial velocity contours at prediffuser exit (X4): (a)minj=30%, (b)minj=50%, (c)minj=70% (height=65.9mm, sector angle Δθ=18deg (8-OGV passages))




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