0
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.

FIGURES IN THIS ARTICLE
<>
Copyright © 2008 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 2

Measurement planes

Grahic Jump Location
Figure 4

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

Grahic Jump Location
Figure 5

Rig inlet axial velocity profile (X1)

Grahic Jump Location
Figure 6

Pitch averaged profiles at rotor exit (X2)

Grahic Jump Location
Figure 7

Rotor exit (X2) static pressure

Grahic Jump Location
Figure 8

OGV exit (reference) total pressure

Grahic Jump Location
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))

Grahic Jump Location
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))

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In