TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Enhanced External Aerodynamic Performance of a Generic Combustor Using An Integrated OGV/Prediffuser Design Technique

[+] Author and Article Information
A. Duncan Walker

Dept. of Aero. and Auto. Engineering, Loughborough University Loughborough, LE11 3TU, United Kingdoma.d.walker@lboro.ac.uk

Jon F. Carrotte, James J. McGuirk

Dept. of Aero. and Auto. Engineering, Loughborough University Loughborough, LE11 3TU, United Kingdom

J. Eng. Gas Turbines Power 129(1), 80-87 (Feb 01, 2006) (8 pages) doi:10.1115/1.2364008 History: Received October 01, 2005; Revised February 01, 2006

In this paper we use experimental measurements to characterize the extent that improved the external aerodynamic performance (reduced total pressure loss, increased flow quality) of a gas-turbine combustion system may be achieved by adopting an integrated OGV/prediffuser technique. Two OGV/prediffuser combinations were tested. The first is a datum design corresponding to a conventional design approach, where the OGV and prediffuser are essentially designed in isolation. The second is an “integrated” design where the OGV blade shape has been modified, following recommendations of earlier CFD work (Final Report No. TT03R01, 2003), to produce a secondary flow/wake structure that allows the prediffuser to operate at a higher area ratio without boundary layer separation. This is demonstrated to increase static pressure recovery and reduce dump losses. Experimental measurements are presented on a fully annular rig. Several traverse planes are used to gather five-hole probe data that allow the flow structure through the OGV, at the inlet and exit of the prediffuser, and in the inner/outer annulus supply ducts to be examined. Both overall performance measures (loss coefficients) and measures of flow uniformity and quality are used to demonstrate that the integrated design is superior.

Copyright © 2007 by American Society of Mechanical Engineers
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Figure 1

Experimental facility—Test cell schematic

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Figure 2

Experimental facility—Test section photograph

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Figure 3

Test section showing traverse plane locations

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Figure 4

Datum (top), integrated (middle) geometries, and cross-section comparison (bottom)

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Figure 5

Datum and integrated geometries on diffuser chart

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Figure 6

Flame tube configuration and mass flow split

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Figure 7

Axial velocity profile at rotor inlet (X1)

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Figure 8

Axial velocity and total pressure profiles (IOGV) at rotor exit (X2)

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Figure 9

OGV exit (X3) axial velocity contours and secondary flow vectors: Datum (left); IOGV (right)

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Figure 10

Axial velocity contours and secondary flow vectors at pre-diffuser exit (X4) datum design 2 OGV sector (left); 8 OGV sector (right)

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Figure 11

Axial velocity contours and secondary flow vectors at prediffuser exit (X4) datum design (left); integrated design (right)

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Figure 12

Axial velocity and pitch angle profiles at X4

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Figure 13

Circumferentially averaged pitch and yaw angles in annuli: inner (XI5) top; outer (XO5) bottom




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