0
Research Papers

Influence of Combustor Flow With Swirl on Integrated Combustor Vane Concept Full-Stage Performance

[+] 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 August 20, 2017; final manuscript received August 26, 2017; published online October 17, 2017. Editor: Kenneth Hall.

J. Turbomach 140(1), 011002 (Oct 17, 2017) (8 pages) Paper No: TURBO-17-1124; doi: 10.1115/1.4037820 History: Received August 20, 2017; Revised August 26, 2017

The integrated combustor vane concept for power generation gas turbines with can combustors has been shown to have significant benefits compared to conventional nozzle guide vanes (NGV). Aerodynamic loss, heat transfer levels, and cooling requirements are reduced while stage efficiency is improved by approximately 1.5% (for a no-swirl scenario). Engine realistic combustor flow with swirl, however, leads to increased turning nonuniformity downstream of the integrated vanes. This paper thus illustrates the altered integrated vane stage performance caused by inlet swirl. The study shows a distinct performance penalty for the integrated vane rotor as a result of increased rotor incidence and the rotor's interaction with the residual swirl core. The stage efficiency advantage of the integrated combustor vane concept compared to the conventional design is thus reduced to 0.7%. It is furthermore illustrated how integrated vane profiling is suitable to reduce the turning variation across the span downstream of the vane, further improve stage efficiency (in this case by 0.23%) and thus mitigate the distinct impact of inlet swirl on integrated vane stage performance.

FIGURES IN THIS ARTICLE
<>
Copyright © 2018 by ASME
Your Session has timed out. Please sign back in to continue.

References

Schwab, J. R. , Stabe, R. G. , and Whitney, W. J. , 1983, “ Analytical and Experimental Study of Flow Through an Axial Turbine Stage With Nonuniform Inlet Radial Temperature Profiles,” AIAA Paper No. 83-1175.
Butler, T. L. , Sharma, O. P. , Joslyn, H. D. , and Dring, R. P. , 1989, “ Redistribution of Inlet Temperature Distortion in an Axial Flow Turbine Stage,” J. Propul. Power, 5(1), pp. 64–71. [CrossRef]
Haldeman, C. , 1989, “ An Experimental Study of Radial Temperature Profile Effects on Turbine Tip Shroud Heat Transfer,” M.S. thesis, Massachusetts Institute of Technology, Cambridge, MA.
Shang, T. , and Epstein, A. H. , 1996, “ Analysis of Hot Streak Effects on Turbine Rotor Heat Load,” ASME Paper No. 96-GT-118.
Barringer, M. D. , Thole, K. A. , and Polanka, M. D. , 2009, “ Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes,” ASME J. Turbomach., 131(2), p. 021010. [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]
Qureshi, I. , Smith, A. D. , and Povey, T. , 2012, “ HP Vane Aerodynamics and Heat Transfer in the Presence of Aggressive Inlet Swirl,” ASME J. Turbomach., 135(2), p. 021040. [CrossRef]
Qureshi, I. , Beretta, A. , Chana, K. S. , and Povey, T. , 2012, “ Effect of Aggressive Inlet Swirl on Heat Transfer and Aerodynamics in an Unshrouded Transonic HP Turbine,” ASME J. Turbomach., 134(6), p. 061023. [CrossRef]
Qureshi, I. , and Povey, T. , 2011, “ A Combustor-Representative Swirl Simulator for a Transonic Turbine Research Facility,” Proc. Inst. Mech. Eng., Part G, 225(7), pp. 737–748. [CrossRef]
Beard, P. , Smith, A. , and Povey, T. , 2013, “ Effect of Combustor Swirl on Transonic High Pressure Turbine Efficiency,” ASME J. Turbomach., 136(1), p. 011002. [CrossRef]
Schmid, G. , Krichbaum, A. , Werschnik, H. , and Schiffer, H. , 2014, “ 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]
Rahim, A. , and He, L. , 2015, “ Rotor Blade Heat Transfer of High Pressure Turbine Stage Under Inlet Hot-Streak and Swirl,” ASME J. Eng. Gas Turbines Power, 137(6), p. 062601. [CrossRef]
Jacobi, S. , and Rosic, B. , 2015, “ Development and Aerothermal Investigation of Integrated Combustor Vane Concept,” ASME J. Turbomach., 138(1), p. 011002. [CrossRef]
Jacobi, S. , and Rosic, B. , 2016, “ Thermal Investigation of Integrated Combustor Vane Concept Under Engine-Realistic Conditions,” ASME J. Turbomach., 139(2), p. 021005. [CrossRef]
Jacobi, S. , Ishizaka, K. , and Rosic, B. , 2017, “ Full-Stage Performance of Integrated Combustor Vane Concept,” Global Power and Propulsion Society's Forum (GPPS), Shanghai, China, Oct. 30–Nov. 1, Paper No. GPPF-2017-147.
Jacobi, S. , 2013, “ Influence of Lean Premixed Combustor Geometry on the First Turbine Vanes' Aerothermal Performance,” M.Sc. thesis, ETH Zürich, Zürich, Switzerland.

Figures

Grahic Jump Location
Fig. 1

Schematic of conventional vane stage (a) and integrated vane stage (b), and mesh at integrated vane—rotor interface (c)

Grahic Jump Location
Fig. 2

Measured dimensionless total pressure distribution (top), pitchwise-averaged yaw (bottom left), and spanwise-averaged pitch (bottom right) at the combustor transition duct exit

Grahic Jump Location
Fig. 3

Influence of swirl on stage efficiency loss for conventional and integrated vanes

Grahic Jump Location
Fig. 4

Instantaneous entropy function at midspan (top), sliding interface (middle), and downstream of rotor (bottom) for conventional vane stage simulation without (a) and with (b) inlet swirl

Grahic Jump Location
Fig. 5

Time- and pitchwise-averaged turning at rotor sliding interface for conventional (black), integrated (green), and profiled integrated (red) vane stage simulation without (solid) and with (dotted) inlet swirl

Grahic Jump Location
Fig. 6

Instantaneous streamtraces on integrated vane rotor for a no-swirl (a) and a swirl (b) case

Grahic Jump Location
Fig. 7

Instantaneous entropy function at 33% span (top), sliding interface (middle), and downstream of rotor (bottom) for integrated vane stage simulation without (a) and with (b) inlet swirl

Grahic Jump Location
Fig. 8

Time- and pitchwise-averaged entropy function at rotor in- and outlet for conventional (black), integrated (green), and profiled integrated (red) vane stage simulation with inlet swirl

Grahic Jump Location
Fig. 9

Schematic of integrated vane profiling: (a) two-dimensional integrated vane and (b) profiled integrated vane

Grahic Jump Location
Fig. 10

Instantaneous entropy function at 33% span (top) and axial cut downstream of rotor (bottom) for profiled integrated vane stage simulation with swirl

Grahic Jump Location
Fig. 11

Instantaneous streamtraces on integrated (a) and profiled integrated (b) vane rotor for the swirl case

Tables

Errata

Discussions

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