0
Research Papers

Aerothermal Performance of a Nozzle Vane Cascade With a Generic Nonuniform Inlet Flow Condition—Part I: Influence of Nonuniformity Location

[+] Author and Article Information
A. Perdichizzi

Dipartimento di Ingegneria e Scienze Applicate,
Università degli Studi di Bergamo,
Dalmine, BG 24044, Italy
e-mail: antonio.perdichizzi@unibg.it

H. Abdeh

Dipartimento di Ingegneria e Scienze Applicate,
Università degli Studi di Bergamo,
Dalmine, BG 24044, Italy
e-mail: hamed.abdeh@unibg.it

G. Barigozzi

Dipartimento di Ingegneria e Scienze Applicate,
Università degli Studi di Bergamo,
Dalmine, BG 24044, Italy
e-mail: giovanna.barigozzi@unibg.it

M. Henze, J. Krueckels

Ansaldo Energia Switzerland Ltd.,
Baden 5401, Switzerland

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 7, 2016; final manuscript received September 22, 2016; published online November 8, 2016. Editor: Kenneth Hall.

J. Turbomach 139(3), 031002 (Nov 08, 2016) (9 pages) Paper No: TURBO-16-1230; doi: 10.1115/1.4034816 History: Received September 07, 2016; Revised September 22, 2016

In this paper, the modifications induced by the presence of an inlet flow nonuniformity on the aerodynamic performance of a nozzle vane cascade are experimentally assessed. Tests were carried out in a six vane linear cascade whose profile is typical of a first stage nozzle guide vane of a modern heavy-duty gas turbine. An obstruction was located in the wind tunnel inlet section to produce a nonuniform flow upstream of the leading edge plane. The cascade was tested in an atmospheric wind tunnel at an inlet Mach number Ma1 = 0.12, with a high turbulence intensity (Tu1 = 9%) and variable obstruction tangential and axial positions, as well as tangential extension. The presented results show that an inlet flow nonuniformity influences the stagnation point position when it faces the vane leading edge from the suction side. A relevant increase of both 2D and secondary losses is observed when the nonuniformity is aligned to the vane leading edge. When it is instead located in between the passage, it does not affect the stagnation point location, in the meanwhile allowing a reduction in the secondary loss.

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

References

Barringer, M. , Thole, K. A. , and Polanka, M. D. , 2009, “ An Experimental Study of Combustor Exit Profile Shapes on Endwall Heat Transfer in High Pressure Turbine Vanes,” ASME J. Turbomach., 131(2), p. 021009. [CrossRef]
Hermanson, K. S. , and Thole, K. A. , 2002, “ Effect of Nonuniform Inlet Conditions on Endwall Secondary Flows,” ASME J. Turbomach., 124(4), pp. 623–631. [CrossRef]
Butler, T. L. , Sharma, O. P. , Joslyn, H. D. , and Dring, R. P. , 1989, “ Redistribution of an Inlet Temperature Distortion in an Axial Flow Turbine Stage,” J. Propul., 5(1), pp. 64–71. [CrossRef]
Stitzel, S. , and Thole, K. A. , 2004, “ Flow Field Computations of Combustor-Turbine Interactions Relevant to a Gas Turbine Engine,” ASME J. Turbomach., 126(1), pp. 122–129. [CrossRef]
Povey, T. , Chana, K. S. , Jones, T. V. , and Hurrion, J. , 2007, “ The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study,” ASME J. Turbomach., 129(1), pp. 32–43. [CrossRef]
Mathison, R. M. , Haldeman, C. W. , and Dunn, M. G. , 2012, “ Aerodynamic and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration,” ASME J. Turbomach., 134(1), p. 011006. [CrossRef]
Jenkins, S. C. , Varadarajan, K. , and Bogard, D. G. , 2004, “ The Effects of High Mainstream Turbulence and Turbine Vane Film Cooling on the Dispersion of a Simulated Hot Streak,” ASME J. Turbomach., 126(1), pp. 203–211. [CrossRef]
Jenkins, S. C. , and Bogard, D. G. , 2009, “ Superposition Predictions of the Reduction of Hot Streaks by Coolant From a Film-Cooled Guide Vane,” ASME J. Turbomach., 131(9), p. 041002. [CrossRef]
Insinna, M. , Griffini, D. , Salvadori, S. , and Martelli, F. , 2014, “ Conjugate Heat Transfer Analysis of a Film Cooled High-Pressure Turbine Vane Under Realistic Combustor Exit Flow Conditions,” ASME Paper No. GT2014-25280.
Insinna, M. , Griffini, D. , Salvadori, S. , and Martelli, F. , 2015, “ Effects of Realistic Inflow Conditions on the Aero-Thermal Performance of a Film-Cooled Vane,” 11th European Turbomachinery Conference (ETC11), Madrid, Spain, Mar. 23–27.
Mazzoni, C. M. , Klostermeier, C. , and Rosic, B. , 2015, “ Combustor Wall Axial Location Effects on First Vane Leading Edge Cooling,” J. Propul. Power, 31(4), pp. 1094–1106. [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]
Perdichizzi, A. , and Dossena, V. , 1993, “ Incidence Angle and Pitch-Chord Effects on Secondary Flows Downstream of a Turbine Cascade,” ASME J. Turbomach., 115(3), pp. 383–391. [CrossRef]
Naik, S. , Krueckels, J. , Gritsch, M. , and Schnieder, M. , 2014, “ Multirow Film Cooling Performances of a High Lift Blade and Vane,” ASME J. Turbomach., 136(5), p. 051003. [CrossRef]
Barigozzi, G. , Perdichizzi, A. , Henze, M. , and Krueckels, J. , 2015, “ Aerodynamic and Heat Transfer Characterization of a Nozzle Vane Cascade With and Without Platform Cooling,” ASME Paper No. GT2015-42845.
Barigozzi, G. , Abdeh, H. , Perdichizzi, A. , Henze, M. , and Krueckels, J. , 2016, “ Aero-Thermal Performance of a Nozzle Vane Cascade With a Generic Non Uniform Inlet Flow Condition—Part II: Influence of Purge and Film Cooling Injection,” ASME Paper No. GT2016-57445.
Gregory-Smith, D. G. , Graves, C. P. , and Walsh, J. A. , 1988, “ Growth of Secondary Losses and Vorticity in an Axial Turbine Cascade,” ASME J. Turbomach., 110(1), pp. 1–8. [CrossRef]
Eckert, E. R. G. , 1986, “ Energy Separation in Fluid Streams,” Int. Commun. Heat Mass Transfer, 13(2), pp. 127–143. [CrossRef]
Carscallen, W. E. , Currie, T. C. , Hogg, S. I. , and Gostelow, J. P. , 1999, “ Measurement and Computation of Energy Separation in the Vortical Wake Flow of a Turbine Nozzle Cascade,” ASME J. Turbomach., 121(4), pp. 703–707. [CrossRef]

Figures

Grahic Jump Location
Fig. 1

The wind tunnel assembly

Grahic Jump Location
Fig. 2

Cascade model and blockage

Grahic Jump Location
Fig. 3

Inlet boundary layer (X/cax = −1.6—uniform)

Grahic Jump Location
Fig. 4

Inlet flow: (a) velocity, (b) angle, and (c) Tu distributions at X/cax = −0.3 and Z/H = 0.5 (a = 0.7cax and w = 0.3 s)

Grahic Jump Location
Fig. 5

Vane load for variable t (a = 0.7cax and w = 0.3s): (a) vane #1 and (b) vane #2

Grahic Jump Location
Fig. 6

Ma distributions at Z/H = 0.5 (a = 0.7cax and w = 0.3s): (a) uniform, (b) t = 0s, and (c) t = 0.5s

Grahic Jump Location
Fig. 7

Tu distribution at Z/H = 0.5 (a = 0.7cax and w = 0.3s): (a) t = 0s and (b) t = 0.5s

Grahic Jump Location
Fig. 8

pt,2/pt,1 distributions at Z/H = 0.5 and X/cax = 1.5 (a = 0.7cax and w = 0.3s)

Grahic Jump Location
Fig. 9

Platform oil and dye surface flow visualizations (a = 0.7cax and w = 0.3s): (a) uniform, (b) t = 0s, (c) t = 0.25s, (d) t = 0.5s, (e) t = 0.75s

Grahic Jump Location
Fig. 10

Platform TLC color map

Grahic Jump Location
Fig. 11

ζ distributions at X/cax = 1.5 (a = 0.7cax and w = 0.3s): (a) uniform inlet, (b) t = 0s, (c) t = 0.25s, (d) t = 0.5s, (e) t = 0.75s, and (f) t = 1s

Grahic Jump Location
Fig. 12

Ω distributions at X/cax = 1.5 (a = 0.7cax and w = 0.3s): (a) uniform inlet, (b) 0s, (c) 0.25s, (d) 0.5s, (e) 0.75s, and (f) 1s

Grahic Jump Location
Fig. 13

Vane #1 load distribution for variable a and w (t = 0s)

Grahic Jump Location
Fig. 14

Platform surface flow visualizations (t = 0s): (a) a = 0.54cax (w = 0.3s), (b) a = 0.96cax (w = 0.3s), and (c) w = 0.24s (a = 0.7cax)

Grahic Jump Location
Fig. 15

ζ distributions for variable axial position a (t = 0s and w = 0.3s): (a) a = 0.54cax and (b) a = 0.96cax

Grahic Jump Location
Fig. 16

Mass-averaged loss coefficient: influence of (a) t and (b) a

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