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.

Copyright © 2016 by ASME
Your Session has timed out. Please sign back in to continue.


Hada, S. , Yuri, M. , Masada, J. , Ito, E. , and Tsukagoshi, K. , 2012, “ Evolution and Future Trend of Large Frame Gas Turbines: A New 1600 Degree C, J Class Gas Turbine,” ASME Paper No. GT2012-68574.
Salvadori, S. , Riccio, G. , Insinna, M. , and Martelli, F. , 2012, “ Analysis of Combustor/Vane Interaction With Decoupled and Loosely Coupled Approaches,” ASME Paper No. GT2012-69038.
Cha, C. M. , Hong, S. , Ireland, P. T. , Denman, P. , and Savarianandam, V. , 2012, “ Experimental and Numerical Investigation of Combustor-Turbine Interaction Using an Isothermal, Nonreacting Tracer,” ASME J. Eng. Gas Turbines Power, 134(8), p. 081501. [CrossRef]
Ames, F. E. , Wang, C. , and Barbot, P. A. , 2003, “ Measurement and Prediction of the Influence of Catalytic and Dry Low NOx Combustor Turbulence on Vane Surface Heat Transfer,” ASME J. Turbomach., 125(2), pp. 221–231. [CrossRef]
Cha, C. M. , Hong, S. , Ireland, P. T. , Denman, P. , and Savarianandam, V. , 2012, “ Turbulence Levels are High at the Combustor-Turbine Interface,” ASME Paper No. GT2012-69130.
Schmid, G. , Krichbaum, A. , Werschnik, H. , and Schiffer, H.-P. , 2014, “ Gt2014-26716 the Impact of Realistic Inlet Swirl in a 1.5 Stage Axial Turbine,” ASME Paper No. GT2014-26716.
Khanal, B. , He, L. , Northall, J. , and Adami, P. , 2013, “ Analysis of Radial Migration of Hot-Streak in Swirling Flow Through High-Pressure Turbine Stage,” ASME J. Turbomach., 135(4), p. 041005. [CrossRef]
Thole, K. , 2006, “ Airfoil Endwall Heat Transfer,” The Gas Turbine Handbook, National Energy Technology Laboratory, DOE, Morgantown, WV.
Rosic, B. , Denton, J. , Horlock, J. , and Uchida, S. , 2010, “ Integrated Combustor and Vane Concept in Gas Turbines,” ASME Paper No. GT2010-23170.
Mazzoni, C. , 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.
Aslanidou, I. , Rosic, B. , Kanjirakkad, V. , and Uchida, S. , 2012, “ Leading Edge Shielding Concept in Gas Turbines With Can Combustors,” ASME Paper No. GT2012-68644.
Denton, J. , and Pullan, G. , 2012, “ A Numerical Investigation Into the Sources of Endwall Loss in Axial Flow Turbines,” ASME Paper No. GT2012-69173.
Sieverding, C. , 1993, “ Recent Progress in the Understanding of Basic Aspects of Secondary Flows in Turbine Blade Passages,” ASME J. Eng. Gas Turbines Power, 107(2), pp. 248–257. [CrossRef]
Gregory-Smith, D. , Graves, C. , and Walsh, J. , 1985, “ Growth of Secondary Losses and Vorticity in an Axial Turbine Cascade,” ASME J. Eng. Gas Turbines Power, 107(2), pp. 248–257.
Denton, J. D. , 1993, “ The 1993 Igti Scholar Lecture: Loss Mechanisms in Turbomachines,” ASME J. Turbomach., 115(4), pp. 621–656. [CrossRef]
Denton, J. , and Xu, L. , 1999, “ The Exploitation of Three-Dimensional Flow in Turbomachinery Design,” Proc. Inst. Mech. Eng., Part C: J. Mech. Eng. Sci., 213(2), pp. 125–137. [CrossRef]
Luque, S. , Kanjirakkad, V. , Aslanidou, I. , Lubbock, R. , and Rosic, B. , 2014, “ A New Experimental Facility to Investigate Combustor-Turbine Interactions in Gas Turbines With Multiple Can Combustors,” ASME Paper No. GT2014-26987.
Oldfield, M. , 2008, “ Impulse Response Processing of Transient Heat Transfer Gauge Signals,” ASME J. Turbomach., 130(2), p. 021023. [CrossRef]
Roach, P. , 1987, “ The Generation of Nearly Isotropic Turbulence by Means of Grids,” Int. J. Heat Fluid Flow, 8(2), pp. 82–92. [CrossRef]
Denton, J. D. , 1983, “ An Improved Time-Marching Method for Turbomachinery Flow Calculation,” J. Eng. Power, 105(3), pp. 514–521. [CrossRef]
Mazzoni, C. , Luque, S. , and Rosic, B. , 2015, “ Capabilities of Thermal Wall Functions to Predict Heat Transfer on the NGVS of a Gas Turbine With Multiple Can Combustors,” ASME Paper No. GT2015-43515.


Grahic Jump Location
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

Grahic Jump Location
Fig. 2

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

Grahic Jump Location
Fig. 3

Schematic domain of CV and IV designs

Grahic Jump Location
Fig. 4

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

Grahic Jump Location
Fig. 5

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

Grahic Jump Location
Fig. 6

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

Grahic Jump Location
Fig. 7

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

Grahic Jump Location
Fig. 8

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

Grahic Jump Location
Fig. 9

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

Grahic Jump Location
Fig. 10

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

Grahic Jump Location
Fig. 11

Growth of total pressure loss coefficient through linear CFD domains

Grahic Jump Location
Fig. 12

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

Grahic Jump Location
Fig. 13

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

Grahic Jump Location
Fig. 14

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

Grahic Jump Location
Fig. 15

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

Grahic Jump Location
Fig. 16

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

Grahic Jump Location
Fig. 17

IV annular full-stage domain and mesh

Grahic Jump Location
Fig. 18

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

Grahic Jump Location
Fig. 19

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

Grahic Jump Location
Fig. 20

Time-averaged efficiency loss through CV and IV stage configurations

Grahic Jump Location
Fig. 21

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




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