0
Research Papers

Aerothermal Performance of Shielded Vane Design

[+] Author and Article Information
Ioanna Aslanidou

Osney Thermofluids Laboratory,
Department of Engineering Science,
University of Oxford,
Oxford OX2 0ES, UK
e-mail: ioanna.aslanidou@mdh.se

Budimir Rosic

Osney Thermofluids Laboratory,
Department of Engineering Science,
University of Oxford,
Oxford OX2 0ES, UK

1Present address: Future Energy Centre, Mälardalen University, Västerås 721 23, Sweden.

2Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 2, 2016; final manuscript received May 30, 2017; published online July 19, 2017. Assoc. Editor: Rolf Sondergaard.

J. Turbomach 139(11), 111003 (Jul 19, 2017) (11 pages) Paper No: TURBO-16-1267; doi: 10.1115/1.4037126 History: Received October 02, 2016; Revised May 30, 2017

This paper presents an experimental investigation of the concept of using the combustor transition duct wall to shield the nozzle guide vane leading edge. The new vane is tested in a high-speed experimental facility, demonstrating the improved aerodynamic and thermal performance of the shielded vane. The new design is shown to have a lower average total pressure loss than the original vane, and the heat transfer on the vane surface is overall reduced. The peak heat transfer on the vane leading edge–endwall junction is moved further upstream, to a region that can be effectively cooled as shown in previously published numerical studies. Experimental results under engine-representative inlet conditions showed that the better performance of the shielded vane is maintained under a variety of inlet conditions.

Copyright © 2017 by ASME
Your Session has timed out. Please sign back in to continue.

References

Mazzoni, C. M. , Rosic, B. , and Klostermeier, C. , 2015, “ Combustor Wall Axial Location Effects on First Vane Leading-Edge Cooling,” AIAA J. Propul. Power, 31(4), pp. 1094–1106.
Rosic, B. , Denton, J. D. , Horlock, J. H. , and Uchida, S. , 2011, “ Integrated Combustor and Vane Concept in Industrial Gas Turbines,” ASME J. Turbomach., 134(3), p. 031005. [CrossRef]
Mazzoni, C. M. , Klostermeier, C. , and Rosic, B. , 2014, “ Influence of Large Wake Disturbances Shed From the Combustor Wall on the Leading Edge Film Cooling,” ASME J. Eng. Gas Turbines Power, 136(8), p. 081503. [CrossRef]
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. , 2013, “ Fundamental Gas Turbine Heat Transfer,” ASME J. Therm. Sci. Eng. Appl., 5(2), p. 021007. [CrossRef]
Radomsky, R. W. , and Thole, K. A. , 2002, “ Detailed Boundary Layer Measurements on a Turbine Stator Vane at Elevated Freestream Turbulence Levels,” ASME J. Turbomach., 124(1), pp. 107–118. [CrossRef]
Ames, F. E. , and Plesniak, M. W. , 1997, “ The Influence of Large-Scale, High-Intensity Turbulence on Vane Aerodynamic Losses, Wake Growth, and the Exit Turbulence Parameters,” ASME J. Turbomach., 119(2), pp. 182–192. [CrossRef]
Zhang, Q. , Sandberg, D. , and Ligrani, P. M. , 2005, “ Mach Number and Freestream Turbulence Effects on Turbine Vane Aerodynamic Losses,” J. Propul. Power, 21(6), pp. 988–996. [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]
Nasir, S. , Carullo, J. S. , Ng, W. , Thole, K. A. , Wu, H. , Zhang, L. J. , and Moon, H. K. , 2009, “ Effects of Large Scale High Freestream Turbulence and Exit Reynolds Number on Turbine Vane Heat Transfer in a Transonic Cascade,” ASME J. Turbomach., 131(2), p. 021021. [CrossRef]
Jouini, D. B. M. , Sjolander, S. A. , and Moustapha, S. H. , 2001, “ Aerodynamic Performance of a Transonic Turbine Cascade at Off-Design Conditions,” ASME J. Turbomach., 123(3), pp. 510–518. [CrossRef]
Weiss, A. P. , and Fottner, L. , 1995, “ The Influence of Load Distribution on Secondary Flow in Straight Turbine Cascades,” ASME J. Turbomach., 117(1), pp. 133–141. [CrossRef]
Benner, M. W. , Sjolander, S. A. , and Moustapha, S. H. , 2004, “ The Influence of Leading-Edge Geometry on Secondary Losses in a Turbine Cascade at the Design Incidence,” ASME J. Turbomach., 126(2), pp. 277–287. [CrossRef]
Qureshi, I. , Beretta, A. , Chana, K. , 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. , 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]
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]
Miller, R. J. , and Denton, J. D. , 2012, Loss Mechanisms in Turbomachines, Cambridge Turbomachinery Course, University of Cambridge, Cambridge, UK, pp. 79–116.
Kang, M. B. , Kohli, A. , and Thole, K. A. , 1999, “ Heat Transfer and Flowfield Measurements in the Leading Edge Region of a Stator Vane Endwall,” ASME J. Turbomach., 121(3), pp. 558–568. [CrossRef]
Nealy, D. A. , Mihelc, M. S. , Hylton, L. D. , and Gladden, H. J. , 1984, “ Measurements of Heat Transfer Distribution Over the Surfaces of Highly Loaded Turbine Nozzle Guide Vanes,” ASME J. Eng. Gas Turbines Power, 106(1), pp. 149–158. [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), pp. 021019–021027. [CrossRef]
Luque, S. , Kanjirakkad, V. , Aslanidou, I. , Lubbock, R. , Rosic, B. , and Uchida, S. , 2015, “ A New Experimental Facility to Investigate Combustor-Turbine Interactions in Gas Turbines With Multiple Can Combustors,” ASME J. Eng. Gas Turbines Power, 137(5), p. 051503. [CrossRef]
Gillespie, D. R. H. , 1996, “ Intricate Internal Cooling Systems for Gas Turbine Blading,” Ph.D. thesis, University of Oxford, Oxford, UK. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365831
Oldfield, M. L. G. , 2008, “ Impulse Response Processing of Transient Heat Transfer Gauge Signals,” ASME J. Turbomach., 130(2), p. 021023. [CrossRef]
Aslanidou, I. , 2015, “ Combustor and Turbine Aerothermal Interactions in Gas Turbines With Can Combustors,” Ph.D. thesis, University of Oxford, Oxford, UK. https://ora.ox.ac.uk/objects/uuid:b1527fd0-8e54-4831-8625-32722141511e
Corriveau, D. , and Sjolander, S. A. , 2004, “ Influence of Loading Distribution on the Performance of Transonic High Pressure Turbine Blades,” ASME J. Turbomach., 126(2), pp. 288–296. [CrossRef]
Roach, P. E. , 1987, “ The Generation of Nearly Isotropic Turbulence by Means of Grids,” Int. J. Heat Fluid Flow, 8(2), pp. 82–92. [CrossRef]
Jacobi, S. , 2013, “ Influence of Lean Premixed Combustor Geometry on the First Turbine Vanes Aerothermal Performance,” Master's thesis, Swiss Federal Institute of Technology (ETH) Zurich, Zurich, Switzerland.

Figures

Grahic Jump Location
Fig. 1

Schematic view of experimental facility including details of the working section [21]

Grahic Jump Location
Fig. 2

CAD sketch with original and shielded cascade for the experimental facility: (a) original cascade and (b) shielded cascade

Grahic Jump Location
Fig. 3

View points of the cascade for IR measurements: (a) view points from the sides (1 and 2) and downstream (3) and (b) view points from above and upstream (4) and above and downstream (5)

Grahic Jump Location
Fig. 4

Views of the cascade for IR measurements, corresponding to the viewpoints depicted in Fig. 3: (a) vane pressure side (view 1), (b) vane leading edge (view 2), (c) vane suction side (view 3), (d) hub endwall, viewed from upstream (view 4), and (e) hub endwall, viewed from downstream (view 5)

Grahic Jump Location
Fig. 5

Total pressure loss coefficient downstream of the cascade for the new shielded vane compared to the datum case, experimental result

Grahic Jump Location
Fig. 6

Spatially resolved total pressure loss coefficient downstream of the cascade for low inlet turbulence, experimental result: (a) original vane cascade and (b) shielded vane cascade

Grahic Jump Location
Fig. 7

Mass-weighted average total pressure loss coefficient for the original and the new shielded vane, experimental result

Grahic Jump Location
Fig. 8

Spatially resolved total pressure loss coefficient on the endwall for the original and shielded case, for low inlet turbulence, experimental result: (a) original case and (b) shielded case

Grahic Jump Location
Fig. 9

Isentropic Mach number distribution on the vane surface for 50% span, experimental and numerical result

Grahic Jump Location
Fig. 10

Comparison of yaw angle downstream of the original and the new shielded vane, experimental result: (a) mass-weighted pitchwise average, (b) original vane, and (c) shielded vane

Grahic Jump Location
Fig. 11

Nondimensional temperature contours for the original and the new shielded vane at 50% span, numerical result

Grahic Jump Location
Fig. 12

Nusselt number on the pressure and the suction side of the original and the new shielded vane, numerical result

Grahic Jump Location
Fig. 13

Isentropic Mach number distribution on the original and the new shielded vane at 5% span, numerical result

Grahic Jump Location
Fig. 14

Nusselt number on the vane pressure side for the original and shielded vane (view 1, Fig. 4(a)), experimental result: (a) original vane and (b) shielded vane

Grahic Jump Location
Fig. 15

Leading edge fillet for the original and shielded vane: (a) pressure side and (b) suction side

Grahic Jump Location
Fig. 16

Nusselt number on the vane leading edge for the original and shielded vane (view 2, Fig. 4(b)), experimental result: (a) original vane and (b) shielded vane

Grahic Jump Location
Fig. 17

Nusselt number on the vane suction side for the original and shielded vane (view 3, Fig. 4(c)), experimental result: (a) original vane and (b) shielded vane

Grahic Jump Location
Fig. 18

Comparison of the Nusselt number on the vane suction side for the shielded vane relative to the original (view 3, Fig. 4(c)), experimental result

Grahic Jump Location
Fig. 19

Nusselt number on the vane endwall viewed from upstream for the original and shielded vane (view 4, Fig. 4(d)), experimental result: (a) original vane and (b) shielded vane

Grahic Jump Location
Fig. 20

Nusselt number on the vane endwall viewed from downstream for the original and shielded vane (view 5, Fig. 4(e)), experimental result: (a) original vane and (b) shielded vane

Grahic Jump Location
Fig. 21

Comparison of Nusselt number on the vane endwall viewed from downstream for the shielded vane relative to the original (view 5, Fig. 4(e)), experimental result

Grahic Jump Location
Fig. 22

Nusselt number on the vane endwall between vanes 2 and 3 (view from downstream) for the original and shielded vane, experimental result: (a) original vane and (b) shielded vane

Grahic Jump Location
Fig. 23

Comparison of Nusselt number on the endwall between vanes 2 and 3 (view from downstream) for the shielded vane relative to the original, experimental result

Grahic Jump Location
Fig. 24

Swirl profile upstream of the cascade (viewed from downstream), experimental measurement: (a) total pressure loss, (b) orientation, (c) yaw angle, and (d) pitch angle

Grahic Jump Location
Fig. 25

Comparison of the Nusselt number on the vane suction side between the original and shielded vane with different inlet conditions (view 3, Fig. 4(c)), experimental result: (a) high inlet turbulence and (b) inlet swirl

Grahic Jump Location
Fig. 26

Comparison of the Nusselt number on the vane endwall viewed from downstream between the original and shielded vane with different inlet conditions (view 5, Fig. 4(e)), experimental result: (a) high inlet turbulence and (b) inlet swirl

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