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.

Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.


Horlock, J. H., Watson, D. T., and Jones, T. V., 2001, “Limitations on Gas Turbine Performance Imposed by Large Turbine Cooling Flows,” ASME J. Turbomach., 123(3), pp. 487–494. [CrossRef]
ACARE, 2010, “Aeronautics and Air Transport: Beyond Vision 2020 (Towards 2050),” Advisory Council for Aeronautics Research in Europe, Brussels, Belgium.
Huang, Y., and Yang, V., 2009, “Dynamics and Stability of Lean-Premixed Swirl-Stabilized Combustion,” Prog. Energy Combust. Sci., 35(4), pp. 293–364. [CrossRef]
Han, J. C., Dutta, S., and Ekkad, S. V., 2013, Gas Turbine Heat Transfer and Cooling Technology, 2nd ed., CRC Press, Taylor & Francis Group, New York.
Lakshminarayana, B., 1975, “Effects of Inlet Temperature Gradients on Turbomachinery Performance,” ASME J. Eng. Power, 97(1), pp. 64–71. [CrossRef]
Butler, T. L., Sharma, O. P., Joslyn, H. D., and Dring., R. P., 1989, “Redistribution of an Inlet Temperature Distortion in an Axial Flow Turbine Stage,” J. Propul. Power, 5(1), pp. 64–71. [CrossRef]
Dorney, D. J., Gundy-Burlet, K. L., and Sondak, D. L., 1999, “A Survey of Hot Streak Experiments and Simulations,” Int. J. Turbo Jet-Engines, 16(1), pp. 1–16. [CrossRef]
Povey, T., Chana, K. S., Jones, T. V., and Hurrion, J., 2007, “The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study,” ASME J. Turbomach., 129(1), pp. 32–43. [CrossRef]
Barringer, M. D., Thole, K. A., and Polanka, M. D., 2009, “Effects of Combustor Exit Profiles on Vane Aerodynamic Loading and Heat Transfer in a High Pressure Turbine,” ASME J. Turbomach., 131(2), p. 021008. [CrossRef]
Mathison, R. M., Haldeman, C. W., and Dunn, M. G., 2012, “Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part III: Impact of Hot-Streak Characteristics on Blade Row Heat Flux,” ASME J. Turbomach., 134(1), p. 011008. [CrossRef]
Basol, A. M., Regina, K., Kalfas, A. I., and Abhari, R. S., 2012, “Integrated Combustor Turbine Design for Improved Aerothermal Performance: Effect of Dilution Air Control,” ASME J. Eng. Gas Turbines Power, 134(9), p. 091501. [CrossRef]
Turrell, M. D., Stopford, P. J., Syed, K. J., and Buchanan, E., 2004, “CFD Simulation of the Flow Within and Downstream of a High-Swirl Lean Premixed Gas Turbine Combustor,” ASME Paper No. GT2004-53112. [CrossRef]
Qureshi, I., Smith, A. D., and Povey, T., 2011, “HP Vane Aerodynamics and Heat Transfer in the Presence of Aggressive Inlet Swirl,” ASME Paper No. GT2011-46037. [CrossRef]
Blair, M. F., 1974, “An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls,” ASME J. Heat Transfer, 96(4), pp. 524–529. [CrossRef]
Cardwell, N. D., Sundaram, N., and Thole, K. A., 2007, “The Effects of Varying the Combustor-Turbine Gap,” ASME J. Turbomach., 129(4), pp. 756–764. [CrossRef]
Thrift, A. A., Thole, K. A., and Hada, S., 2012, “Effects of Orientation and Position of the Combustor-Turbine Interface on the Cooling of a Vane Endwall,” ASME J. Turbomach., 134(6), p. 061019. [CrossRef]
Lynch, S. P., Thole, K. A., Kohli, A., Lehane, C., and Praisner, T., 2013, “Endwall Heat Transfer for a Turbine Blade With an Upstream Cavity and Rim Seal,” ASME Paper No. GT2013-94942. [CrossRef]
Mazzoni, C. M., Klostermeier, C., and Rosic, B., 2013, “Influence of Large Wake Disturbances Shed From the Combustor Wall on the Leading Edge Film Cooling,” ASME Paper No. GT2013-94622. [CrossRef]
Aslanidou, I., Rosic, B., Kanjirakkad, V., and Uchida, S., 2013, “Leading Edge Shielding Concept in Gas Turbines With Can Combustors,” ASME J. Turbomach., 135(2), p. 021019. [CrossRef]
Rosic, B., Denton, J. D., Horlock, J. H., and Uchida, S., 2012, “Integrated Combustor and Vane Concept in Gas Turbines,” ASME J. Turbomach., 134(3), p. 031005. [CrossRef]
Hirsch, C., ed., 1993, “Advanced Methods for Cascade Testing,” Advisory Group for Aerospace Research & Development, Neuilly-sur-Seine, France, AGARDograph No. 328.
ISO, 2005, “Measurement of Gas Flow by Means of Critical Flow Venturi Nozzles,” International Organization for Standardization, Geneva, Switzerland, Standard No. ISO 9300.
Jacobi, S., 2013, “Influence of Lean Premixed Combustor Geometry on the First Turbine Vanes' Aerothermal Performance,” Master's thesis, Mechanical and Process Engineering, Swiss Federal Institute of Technology (ETH), Zurich.
Gillespie, D. R. H., 1996, “Intricate Internal Cooling Systems for Gas Turbine Blading,” Ph.D. thesis, Department of Engineering Science, University of Oxford, Oxford, UK.
Ireland, P. T., Neely, A. J., Gillespie, D. R. H., and Robertson, A. J., 1999, “Turbulent Heat Transfer Measurements Using Liquid Crystals,” Int. J. Heat Fluid Flow, 20(4), pp. 355–367. [CrossRef]
Luque, S., and Povey, T., 2011, “A Novel Technique for Assessing Turbine Cooling System Performance,” ASME J. Turbomach., 133(3), p. 031013. [CrossRef]
Oldfield, M. L. G., 2008, “Impulse Response Processing of Transient Heat Transfer Gauge Signals,” ASME J. Turbomach., 130(2), p. 021023. [CrossRef]
Piccini, E., Guo, S. M., and Jones, T. V., 2000, “The Development of a New Direct-Heat-Flux Gauge for Heat-Transfer Facilities,” Meas. Sci. Technol., 11(4), pp. 342–349. [CrossRef]
Schultz, D. L., and Jones, T. V., 1973, “Heat-Transfer Measurements in Short-Duration Hypersonic Facilities,” Advisory Group for Aerospace Research & Development, Neuilly-sur-Seine, France AGARDograph No. 165.
Moffat, R. J., 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1(1), pp. 3–17. [CrossRef]
Buttsworth, D. R., and Jones, T. V., 1998, “A Fast-Response Total Temperature Probe for Unsteady Compressible Flows,” ASME J. Eng. Gas Turbines Power, 120(4), pp. 694–702. [CrossRef]


Grahic Jump Location
Fig. 1

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

Grahic Jump Location
Fig. 2

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

Grahic Jump Location
Fig. 3

Pressure traces during a typical run

Grahic Jump Location
Fig. 4

Temperature traces during a typical run

Grahic Jump Location
Fig. 10

Nusselt number distribution on the SS

Grahic Jump Location
Fig. 11

Nusselt number distribution on the hub endwall

Grahic Jump Location
Fig. 12

Nusselt number distribution on the LE

Grahic Jump Location
Fig. 13

Nusselt number distribution on the PS

Grahic Jump Location
Fig. 9

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

Grahic Jump Location
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

Grahic Jump Location
Fig. 7

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

Grahic Jump Location
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

Grahic Jump Location
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




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