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Research Papers

Development and Aerothermal Investigation of Integrated Combustor Vane Concept

[+] Author and Article Information
Simon Jacobi

Osney Thermo-Fluids Laboratory,
Department of Engineering Science,
University of Oxford,
Oxford OX2 0ES, UK
e-mail: simon.jacobi@eng.ox.ac.uk

Budimir Rosic

Osney Thermo-Fluids Laboratory,
Department of Engineering Science,
University of Oxford,
Oxford OX2 0ES, UK

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 16, 2015; final manuscript received September 3, 2015; published online October 13, 2015. Editor: Kenneth Hall.

J. Turbomach 138(1), 011002 (Oct 13, 2015) (10 pages) Paper No: TURBO-15-1150; doi: 10.1115/1.4031560 History: Received July 16, 2015; Revised September 03, 2015

This paper presents the development and aerothermal investigation of the integrated combustor vane concept for power generation gas turbines with individual can combustors. In this novel concept, first introduced in 2010, the conventional nozzle guide vanes (NGVs) are removed and flow turning is achieved by vanes that extend the combustor walls. The concept was developed using the in-house computational fluid dyanamics (CFD) code TBLOCK. Aerothermal experiments were conducted using a modular high-speed linear cascade, designed to model the flow at the combustor–vane interface. The facility is comprised of two can combustor transition ducts and either four conventional vanes (CVs) or two integrated vanes (IVs). The experimental study validates the linear CFD simulations of the IV development. Annular full-stage CFD simulations, used to evaluate aerodynamics, heat transfer, and stage efficiency, confirm the trends of the linear numerical and experimental results, and thus demonstrate the concept's potential for real gas turbine applications. Results show a reduction of the total pressure loss coefficient at the exit of the stator vanes by more than 25% due to a reduction in profile and endwall loss. Combined with an improved rotor performance demonstrated by unsteady stage simulations, these aerodynamic benefits result in a gain in stage efficiency of above 1%. A distinct reduction in heat transfer coefficient (HTC) levels on vane surfaces, on the order of 25–50%, and endwalls is observed and attributed to an altered state of boundary layer (BL) thickness. The development of IV's endwall- and leading edge (LE)-cooling geometry shows a superior surface coverage of cooling effectiveness, and the cooling requirements for the first vane are expected to be halved. Moreover, by halving the number of vanes, simplifying the design and eliminating the need for vane LE film cooling, manufacturing and development costs can be significantly reduced.

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References

Figures

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Fig. 1

Combustor and turbine interface: (a) F-type gas turbine (Mitsubishi Heavy Industries Ltd.), (b) conventional separated combustor and vane design, and (c) integrated combustor and vane design

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Fig. 2

Working section of the experimental facility including swirler, transition duct, and conventional NGVs (left) or integrated vanes (right)

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Fig. 3

Schematic domain of CV and IV designs

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Fig. 4

Effect of 3D geometry variations on dimensionless total pressure loss for IV; numbers represent averaged values

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Fig. 5

Aerodynamic traverse measurements showing dimensionless total pressure (top) and yaw (bottom) downstream of CV (left) & IV (right)

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Fig. 6

Comparison of pitchwise-averaged aerodynamic traverse measurements and CFD downstream of CV and IV: (a) total pressure and (b) yaw

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Fig. 7

Isentropic Mach number surface distribution for CVs and IV at midspan; lines/dots represent numerical/experimental results

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Fig. 8

Schematic regions of high Mis and BL diffusion on SSs: (a) CV and (b) IV

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Fig. 9

Dimensionless entropy generation rate on hub endwall of CV (top) and IV domain (bottom); surface streamtraces

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Fig. 10

Schematic of endwall BL development: (a) CVs and (b)IV

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Fig. 11

Growth of total pressure loss coefficient through linear CFD domains

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Fig. 12

Schematic of IV's endwall- and LE-cooling geometry

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Fig. 13

Static pressure contour of IV LE-cooling design and seal at midspan; velocity vectors

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Fig. 14

Endwall cooling effectiveness of CV (left) and endwall and LE cooling effectiveness of IV (right)

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Fig. 15

Experimental HTC measurements on CVs' (left) and IV's (right) suction surface

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Fig. 16

HTC for CVs and IV at midspan; lines/dots represent numerical/experimental results

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Fig. 17

IV annular full-stage domain and mesh

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Fig. 18

Predicted aerodynamic contours downstream of IV for annular and linear setup: (a) yaw and (b) total pressure

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Fig. 19

Predicted HTC of annular CV domain (top) and IV domain (bottom)

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Fig. 20

Time-averaged efficiency loss through CV and IV stage configurations

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Fig. 21

Instantaneous entropy function contour of unsteady full-stage CFD for CV (top) and IV (bottom) at midspan

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