Research Papers

Integrated Outlet Guide Vane Design for an Aggressive S-Shaped Compressor Transition Duct

[+] Author and Article Information
A. D. Walker

e-mail: a.d.walker@lboro.ac.uk

J. F. Carrotte

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

M. J. Green

Rolls-Royce PLC,
Derby, DE24 8BJ, UK

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received July 11, 2011; final manuscript received August 2, 2011; published online October 31, 2012. Editor: David Wisler.

J. Turbomach 135(1), 011035 (Oct 31, 2012) (11 pages) Paper No: TURBO-11-1114; doi: 10.1115/1.4006331 History: Received July 11, 2011; Revised August 02, 2011

Within gas turbines the ability to design shorter aggressive S-shaped ducts is advantageous from a performance and weight saving perspective. However, current design philosophies tend to treat the S-shaped duct as an isolated component, neglecting the potential advantages of integrating the design with the upstream or downstream components. In this paper, such a design concept is numerically developed in which the upstream compressor outlet guide vanes are incorporated into the first bend of the S-shaped duct. Positioning the vane row within the first bend imparts a strong radial gradient to the pressure field within the vane passage. Tangential lean and axial sweep are employed such that the vane geometry is modified to exactly match the resulting inclined static pressure field. The integrated design is experimentally assessed and compared to a conventional nonintegrated design on a fully annular low speed test facility incorporating a single stage axial compressor. Several traverse planes are used to gather five-hole probe data which allow the flow structure to be examined through the rotor, outlet guide vane and within the transition ducts. The two designs employ almost identical duct geometry, but integration of the vane row reduces the system length by 21%. Due to successful matching of the static pressure field, the upstream influence of the integrated vane row is minimal and the rotor performance is unchanged. Similarly, the flow development within both S-shaped ducts is similar such that the circumferentially averaged profiles at duct exit are almost identical, and the operation of a downstream component would be unaffected. Overall system loss remains nominally unchanged despite the inclusion of lean and sweep and a reduction in system length. Finally, the numerical design predictions show good agreement with the experimental data thereby successfully validating the design process.

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Fig. 1

Static pressure in an S-shaped duct

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Fig. 2

Integrated OGV concept

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Fig. 3

Integrated OGV design [9]

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Fig. 4

Datum and integrated OGV geometry

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Fig. 5

Static pressure contours of curved flows

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Fig. 6

Static pressure contours in OGV row

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Fig. 7

Normal velocity at OGV exit—design CFD

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Fig. 8

Predicted wall shear stress on inner wall

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Fig. 9

Predicted velocity contours at plane E

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Fig. 10

Predicted velocity contours at duct exit

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Fig. 11

S-duct test section and transverse planes

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Fig. 12

Test rig photographs

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Fig. 13

Local coordinate system

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Fig. 14

Circumferentially averaged profiles at rotor exit

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Fig. 15

Contours at rotor exit

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Fig. 16

Measured contours at OGV exit

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Fig. 17

Circumferentially averaged profiles of normal velocity

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Fig. 18

Wall static pressure (S-duct inlet at x/L = 0)

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Fig. 19

Measured normal velocity contours at plane E

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Fig. 20

Measured velocity contours at duct exit

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Fig. 21

Posttest predicted velocity contours at plane E

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Fig. 22

Posttest predicted velocity contours at exit

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Fig. 23

Development of loss along the ducts (S-duct inlet at x/L = 0)




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