To manage the increasing turbine temperatures of future gas turbines a cooled cooling air system has been proposed. In such a system some of the compressor efflux is diverted for additional cooling in a heat exchanger (HX) located in the bypass duct. The cooled air must then be returned, across the main gas path, to the engine core for use in component cooling. One option is do this within the combustor module and two methods are examined in the current paper; via simple transfer pipes within the dump region or via radial struts in the prediffuser. This paper presents an experimental investigation to examine the aerodynamic impact these have on the combustion system external aerodynamics. This included the use of a fully annular, isothermal test facility incorporating a bespoke 1.5 stage axial compressor, engine representative outlet guide vanes (OGVs), prediffuser, and combustor geometry. Area traverses of a miniature five-hole probe were conducted at various locations within the combustion system providing information on both flow uniformity and total pressure loss. The results show that, compared to a datum configuration, the addition of transfer pipes had minimal aerodynamic impact in terms of flow structure, distribution, and total pressure loss. However, the inclusion of prediffuser struts had a notable impact increasing the prediffuser loss by a third and consequently the overall system loss by an unacceptable 40%. Inclusion of a hybrid prediffuser with the cooled cooling air (CCA) bleed located on the prediffuser outer wall enabled an increase of the prediffuser area ratio with the result that the system loss could be returned to that of the datum level.
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Impact of a Cooled Cooling Air System on the External Aerodynamics of a Gas Turbine Combustion System
A. Duncan Walker,
A. Duncan Walker
Department of Aeronautical and
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: A.D.Walker@lboro.ac.uk
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: A.D.Walker@lboro.ac.uk
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Bharat Koli,
Bharat Koli
Department of Aeronautical and
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: B.Koli@lboro.ac.uk
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: B.Koli@lboro.ac.uk
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Liang Guo,
Liang Guo
Associate Professor
Department of Internal Combustion Engines,
Jilin University,
Changchun 130022, China
e-mail: liangguo@jlu.edu.cn
Department of Internal Combustion Engines,
Jilin University,
Changchun 130022, China
e-mail: liangguo@jlu.edu.cn
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Peter Beecroft,
Peter Beecroft
Rolls-Royce plc,
SIN-A-65,
P.O. Box 31,
Moor Lane,
Derby DE24 8BJ, UK
e-mail: Peter.Beecroft@Rolls-Royce.com
SIN-A-65,
P.O. Box 31,
Moor Lane,
Derby DE24 8BJ, UK
e-mail: Peter.Beecroft@Rolls-Royce.com
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Marco Zedda
Marco Zedda
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A. Duncan Walker
Department of Aeronautical and
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: A.D.Walker@lboro.ac.uk
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: A.D.Walker@lboro.ac.uk
Bharat Koli
Department of Aeronautical and
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: B.Koli@lboro.ac.uk
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, Leicestershire, UK
e-mail: B.Koli@lboro.ac.uk
Liang Guo
Associate Professor
Department of Internal Combustion Engines,
Jilin University,
Changchun 130022, China
e-mail: liangguo@jlu.edu.cn
Department of Internal Combustion Engines,
Jilin University,
Changchun 130022, China
e-mail: liangguo@jlu.edu.cn
Peter Beecroft
Rolls-Royce plc,
SIN-A-65,
P.O. Box 31,
Moor Lane,
Derby DE24 8BJ, UK
e-mail: Peter.Beecroft@Rolls-Royce.com
SIN-A-65,
P.O. Box 31,
Moor Lane,
Derby DE24 8BJ, UK
e-mail: Peter.Beecroft@Rolls-Royce.com
Marco Zedda
Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 1, 2016; final manuscript received September 30, 2016; published online January 10, 2017. Assoc. Editor: Joseph Zelina.
J. Eng. Gas Turbines Power. May 2017, 139(5): 051504 (13 pages)
Published Online: January 10, 2017
Article history
Received:
June 1, 2016
Revised:
September 30, 2016
Citation
Duncan Walker, A., Koli, B., Guo, L., Beecroft, P., and Zedda, M. (January 10, 2017). "Impact of a Cooled Cooling Air System on the External Aerodynamics of a Gas Turbine Combustion System." ASME. J. Eng. Gas Turbines Power. May 2017; 139(5): 051504. https://doi.org/10.1115/1.4035228
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