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

A New Experimental Facility to Investigate Combustor–Turbine Interactions in Gas Turbines With Multiple Can Combustors

[+] Author and Article Information
S. Luque

Department of Engineering Science,
Osney Thermofluids Laboratory,
University of Oxford,
Osney Mead, Oxford OX2 0ES, UK
e-mail: sg.luque@gmail.com

V. Kanjirakkad

Department of Engineering Science,
Osney Thermofluids Laboratory,
University of Oxford,
Osney Mead, Oxford OX2 0ES, UK
e-mail: v.kanjirakkad@sussex.ac.uk

I. Aslanidou

Department of Engineering Science,
Osney Thermofluids Laboratory,
University of Oxford,
Osney Mead, Oxford OX2 0ES, UK
e-mail: ioanna.aslanidou@eng.ox.ac.uk

R. Lubbock

Department of Engineering Science,
Osney Thermofluids Laboratory,
University of Oxford,
Osney Mead, Oxford OX2 0ES, UK
e-mail: roderick.lubbock@eng.ox.ac.uk

B. Rosic

Department of Engineering Science,
Osney Thermofluids Laboratory,
University of Oxford,
Osney Mead, Oxford OX2 0ES, UK
e-mail: budimir.rosic@eng.ox.ac.uk

S. Uchida

Mitsubishi Heavy Industries,
Takasago Research & Development Center,
Takasago, Hyogo 676-8686, Japan
e-mail: sumiu_uchida@mhi.co.jp

1Corresponding author.

2Present address: University of Sussex Thermo-Fluid Mechanics Research Centre, Falmer, Brighton BN1 9QT, UK.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 30, 2014; final manuscript received September 18, 2014; published online December 2, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(5), 051503 (May 01, 2015) (9 pages) Paper No: GTP-14-1316; doi: 10.1115/1.4028714 History: Received June 30, 2014; Revised September 18, 2014; Online December 02, 2014

This paper describes a new modular experimental facility that was purpose-built to investigate flow interactions between the combustor and first stage nozzle guide vanes (NGVs) of heavy duty power generation gas turbines with multiple can combustors. The first stage turbine NGV is subjected to the highest thermal loads of all turbine components and therefore consumes a proportionally large amount of cooling air that contributes detrimentally to the stage and cycle efficiency. It has become necessary to devise novel cooling concepts that can substantially reduce the coolant air requirement but still allow the turbine to maintain its aerothermal performance. The present work aims to aid this objective by the design and commissioning of a high-speed linear cascade, which consists of two can combustor transition ducts and four first stage NGVs. This is a modular nonreactive air test platform with engine realistic geometries (gas path and near gas path), cooling system, and boundary conditions (inlet swirl, turbulence level, and boundary layer). The paper presents the various design aspects of the high pressure (HP) blow down type facility, and the initial results from a wide range of aerodynamic and heat transfer measurements under highly engine realistic conditions.

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References

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Figures

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Fig. 1

Schematic of an industrial gas turbine with multiple can combustors and the first turbine vane, adapted from Ref. [20]

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Fig. 2

Schematic drawing of the experimental facility, including detail of the working section, adapted from Ref. [23]

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Fig. 3

Pressure traces during a typical run

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Fig. 4

Temperature traces during a typical run

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Fig. 10

Nusselt number distribution on the SS

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Fig. 11

Nusselt number distribution on the hub endwall

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Fig. 12

Nusselt number distribution on the LE

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Fig. 13

Nusselt number distribution on the PS

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Fig. 9

Experimentally determined calibration curve for the IR camera, and linear fit employed

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Fig. 8

Heat flux (q·) versus surface temperature (Tw) for a sample pixel, and linear regression from which h and Taw are obtained in a least squares approach

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Fig. 7

Endwall nondimensional static pressure maps: (a) casing endwall and (b) hub endwall

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Fig. 6

Summary of measurements conducted with the five-hole probe 0.17 axial chords downstream of the test vanes: (a) spatially resolved map of nondimensional total pressure loss (p02 = p01) and (b) pitchwise-averaged yaw

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Fig. 5

Isentropic Mach number on the test vanes at three nondimensional span heights (10%, 50%, and 90%): (a) spatially resolved map of nondimensional total pressure loss (p02/p01) and (b) pitchwise-averaged yaw

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