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Research Papers: Gas Turbines: Turbomachinery

Experimental Evaluation of Service-Exposed Nozzle Guide Vane Damage in a Rolls Royce A-250 Gas Turbine

[+] Author and Article Information
D. Bouchard

A.C.F. Associates,
14 Hawley Court,
Bath, ON K0H 1G0, Canada

A. Asghar

Department of Mechanical and
Aerospace Engineering,
Royal Military College of Canada,
19 General Crerar Crescent,
Kingston, ON K7K 7B4, Canada
e-mail: Asad.Asghar@rmc.ca

M. LaViolette

Department of Mechanical and
Aerospace Engineering,
Royal Military College of Canada,
19 General Crerar Crescent,
Kingston, ON K7K 7B4, Canada
e-mail: Laviolette-m@rmc.ca

W. D. E. Allan

Department of Mechanical and
Aerospace Engineering,
Royal Military College of Canada,
19 General Crerar Crescent,
Kingston, ON K7K 7B4, Canada
e-mail: Billy.Allan@rmc.ca

R. Woodason

StandardAero,
1925 Sargent Avenue,
Winnipeg, MB R3H 0E2, Canada
e-mail: ray.woodason@standardaero.com

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received February 25, 2014; final manuscript received March 4, 2014; published online May 2, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(10), 102601 (May 02, 2014) (9 pages) Paper No: GTP-14-1125; doi: 10.1115/1.4027204 History: Received February 25, 2014; Revised March 04, 2014

A unique methodology and test rig was designed to evaluate the degradation of damaged nozzle guide vanes (NGVs) in a transonic annular cascade in the short duration facility at the Royal Military College. A custom test section was designed which featured a novel rotating instrumentation suite. This permitted 360 deg multispan traverse measurements downstream from unmodified turbine NGV rings from a Rolls-Royce/Allison A-250 turbo-shaft engine. The downstream total pressure was measured at four spanwise locations on both an undamaged reference and a damaged test article. Three performance metrics were developed in an effort to determine characteristic signatures for common operational damage such as trailing edge bends or cracked trailing edges. The highest average losses were observed in the root area, while the lowest occurred closer to the NGV tips. The results from this study indicated that multiple spanwise traverses were required to detect localized trailing edge damage. Recommendations are made for future testing and to further develop performance metrics.

Copyright © 2014 by ASME
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References

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Figures

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Fig. 1

Various modes of TE damage on a service-exposed HPT NGV ring

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Fig. 2

The transonic short duration annular cascade rig: photograph on the left, CAD rendering on the right

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Fig. 3

A cross-section view of the total pressure probe tip

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Fig. 4

The longitudinal cross section of an annular cascade and data acquisition system diagram

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Fig. 5

An axial view (left), cross-section view (center), and an exploded view (right) of the total pressure probe assembly

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Fig. 6

The relationship between the probe assembly and the NGV test subject

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Fig. 7

A comparison of the nonsmoothed and SG smoothed total pressure data

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Fig. 8

Reference vane at 50% span (a) total pressure ratios, and (b) area-averaged total pressure loss coefficients (Y)

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Fig. 9

A sketch of the probe layout and axes definition

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Fig. 10

The inlet (left) and outlet (right) faces of the reference vane. (The highlighted vanes have an indent in the LE for a fixture strut.)

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Fig. 11

Reference vane and service-exposed vane at 50% span (a) total pressure ratios, and (b) area-averaged total pressure loss coefficients (Y)

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Fig. 12

Reference vane and service-exposed vane wake-deficits at 50% span: (a) magnitude, and (b) deviation

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Fig. 13

Total pressure ratios of vanes 18 to 24 for the reference and damaged vanes at 50% span

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Fig. 14

TE damage on vanes 2, 3, 22, and 23 highlighting the TE bends and TE cracks

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Fig. 15

Total pressure ratios of vanes 1 to 7 for the reference and damaged vanes at 50% span

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