0
Journal of Turbomachinery | Volume 131 | Issue 2 | Research Paper
Research Papers

An Experimental Study of Combustor Exit Profile Shapes on Endwall Heat Transfer in High Pressure Turbine Vanes

[+] Author and Article Information
M. D. Barringer, K. A. Thole

Department of Mechanical and Nuclear Engineering, Pennsylvania State University, University Park, PA 16802

M. D. Polanka

Turbines Branch, Turbine Engine Division, Air Force Research Laboratory, WPAFB, OH 45433

J. Turbomach 131(2), 021009 (Jan 23, 2009) (10 pages) doi:10.1115/1.2950072 History: Received July 26, 2007; Revised December 05, 2007; Published January 23, 2009
Article
References
Figures
Citing Articles

The design and development of current and future gas turbine engines for aircraft propulsion have focused on operating the high pressure turbine at increasingly elevated temperatures and pressures. The drive toward thermal operating conditions near theoretical stoichiometric limits as well as increasingly stringent requirements on reducing harmful emissions both equate to the temperature profiles exiting combustors and entering turbines becoming less peaked than in the past. This drive has placed emphasis on determining how different types of inlet temperature and pressure profiles affect the first stage airfoil endwalls. The goal of the current study was to investigate how different radial profiles of temperature and pressure affect the heat transfer along the vane endwall in a high pressure turbine. Testing was performed in the Turbine Research Facility located at the Air Force Research Laboratory using an inlet profile generator. Results indicate that the convection heat transfer coefficients are influenced by both the inlet pressure profile shape and the location along the endwall. The heat transfer driving temperature for inlet profiles that are nonuniform in temperature is also discussed.
FIGURES IN THIS ARTICLE
<>
Copyright © 2009 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

1
Zess, G., and Thole, K., 1999, “Computational Design and Experimental Evaluation of Using a Leading Edge Fillet on a Gas Turbine Vane,” ASME Paper No. 2001-GT-0404.
2
Lethander, A., Thole, K., Zess, G., and Wagner, J., 2003, “Optimizing the Vane-Endwall Junction to Reduce Adiabatic Wall Temperatures in a Turbine Vane Passage,” ASME Paper No. GT2003-38940.
3
Hermanson, K., and Thole, K., 2000, “Effect of Inlet Conditions on Endwall Secondary Flows,” J. Propul. Power, 16 (2), pp. 286–296.
4
Munk, M., and Prim, R. C., 1947, “On the Multiplicity of Steady Gas Flows Having the Same Streamline Pattern,” Proc. Natl. Acad. Sci. U.S.A.  [CrossRef], 33 , pp. 137–141.
5
Lakshminarayana, B., 1975, “Effects of Inlet Temperature Gradients on Turbomachinery Performance,” ASME J. Eng. Power, 97 , pp. 64–74.
6
Langston, L. S., 1980, “Crossflows in a Turbine Cascade Passage,” ASME J. Eng. Power, 102 , pp. 866–874.
7
Colban, W. F., Thole, K. A., and Zess, G., 2002, “Combustor-Turbine Interface Studies-Part 1: Endwall Effectiveness Measurements,” ASME Paper No. GT2002-30526.
8
Colban, W. F., Thole, K. A., and Zess, G., 2002, “Combustor-Turbine Interface Studies-Part 2: Flow and Thermal Field Measurements,” ASME Paper No. GT2002-30527.
9
Kost, F., and Nicklas, M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part I-Aerodynamic Measurements,” ASME Paper No. 2001-GT-0145.
10
Kang, M., 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.  [CrossRef], 121 (3), pp. 558–568.
11
Radomsky, R., and Thole, K. A., 2000, “High Freestream Turbulence Effects in the Endwall Leading Edge Region,” ASME J. Turbomach.  [CrossRef], 122 , pp. 699–708.
12
Blair, M. F., 1974, “An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls,” ASME J. Heat Transfer, 96 (4), pp. 524–529.
13
Haldeman, C., and Dunn, M., 2004, “Heat-Transfer Measurements and Predictions for the Vane and Blade of a Rotating High-Pressure Turbine Stage,” ASME J. Turbomach.  [CrossRef], 126 , pp. 101–109.
14
Povey, T., Chana, K., Jones, T., and Hurrion, J., 2005, “The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study,” ASME Paper No. GT2005-69066.
15
Nicklas, M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part II-Heat Transfer and Film-Cooling Effectiveness Measurements,” ASME Paper No. 2001-GT-0146.
16
Graziani, R., Blair, M., Taylor, J., and Mayle, R., 1980, “An Experimental Study of Endwall and Airfoil Surface Heat Transfer in a Large Scale Turbine Blade Cascade,” ASME J. Eng. Power, 102 , pp. 257–267.
17
Haldeman, C. W., Dunn, M. G., MacArthur, C. D., and Murawski, C. G., 1992, “The USAF Advanced Turbine Aerothermal Research Rig (ATARR),” "NATO AGARD Propulsion and Energetics Panel Conference Proceedings", Vol. 527 , Antalya, Turkey.
18
Barringer, M. D., Thole, K. A., and Polanka, M. D., 2007, “Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests,” ASME J. Turbomach.  [CrossRef], 129 (2), pp. 382–393.
19
Jones, T. V., 1995, “The Thin Film Heat Transfer Gauge-A History and New Developments.” Proc. Inst. Mech. Eng., Part C: J. Mech. Eng. Sci., 209 (C510), pp. 150–160.
20
Moffat, R. J., 1982, “Contributions to the Theory of a Single-Sample Uncertainty Analysis,” ASME J. Fluids Eng., 104 , pp. 250–260.
21
Kang, M., and Thole, K. A., 2000, “Flowfield Measurements in the Endwall Region of a Stator Vane,” ASME J. Turbomach.  [CrossRef], 122 , pp. 458–466.
22
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.

Figures

Grahic Jump Location
+Photograph of the TRF facility
View Large  |  Save Figure  |  Download Slide (.ppt)
Photograph of the TRF facility
Figure 1

Photograph of the TRF facility

Grahic Jump Location
+Drawing of the TRF test rig in a vane only configuration with the inlet profile generator
View Large  |  Save Figure  |  Download Slide (.ppt)
Drawing of the TRF test rig in a vane only configuration with the inlet profile generator
Figure 2

Drawing of the TRF test rig in a vane only configuration with the inlet profile generator

Grahic Jump Location
+Photograph of the turbine vane OD endwall instrumented with thin film heat flux gauges
View Large  |  Save Figure  |  Download Slide (.ppt)
Photograph of the turbine vane OD endwall instrumented with thin film heat flux gauges
Figure 3

Photograph of the turbine vane OD endwall instrumented with thin film heat flux gauges

Grahic Jump Location
+Schematic of the OD endwall indicating the locations of the thin film heat flux gauges
View Large  |  Save Figure  |  Download Slide (.ppt)
Schematic of the OD endwall indicating the locations of the thin film heat flux gauges
Figure 4

Schematic of the OD endwall indicating the locations of the thin film heat flux gauges

Grahic Jump Location
+Radial total pressure profiles measured at the vane inlet near the OD
View Large  |  Save Figure  |  Download Slide (.ppt)
Radial total pressure profiles measured at the vane inlet near the OD
Figure 5

Radial total pressure profiles measured at the vane inlet near the OD

Grahic Jump Location
+Radial total temperature profiles corresponding to the pressure profiles in Fig. 5
View Large  |  Save Figure  |  Download Slide (.ppt)
Radial total temperature profiles corresponding to the pressure profiles in Fig. 5
Figure 6

Radial total temperature profiles corresponding to the pressure profiles in Fig. 5

Grahic Jump Location
+Schematics illustrating secondary flow patterns that develop within the vane passage including (a) a cross-passage view near midaxial chord looking downstream, (b) a span view looking toward the endwall, and (c) an isometric view upstream looking downstream
View Large  |  Save Figure  |  Download Slide (.ppt)
Schematics illustrating secondary flow patterns that develop within the vane passage including (a) a cross-passage view near midaxial chord looking downstream, (b) a span view looking toward the endwall, and (c) an isometric view upstream looking downstream
Figure 7

Schematics illustrating secondary flow patterns that develop within the vane passage including (a) a cross-passage view near midaxial chord looking downstream, (b) a span view looking toward the endwall, and (c) an isometric view upstream looking downstream

Grahic Jump Location
+Velocity contours within the vane passage (X∕C=0.35) from Colban (8) showing secondary flow vectors and their corresponding vane inlet total pressure profiles for (a) a turbulent boundary layer and (b) a forward facing IP boundary layer near the endwall
View Large  |  Save Figure  |  Download Slide (.ppt)
Velocity contours within the vane passage (X∕C=0.35) from Colban (8) showing secondary flow vectors and their corresponding vane inlet total pressure profiles for (a) a turbulent boundary layer and (b) a forward facing IP boundary layer near the endwall
Figure 8

Velocity contours within the vane passage (X∕C=0.35) from Colban (8) showing secondary flow vectors and their corresponding vane inlet total pressure profiles for (a) a turbulent boundary layer and (b) a forward facing IP boundary layer near the endwall

Grahic Jump Location
+Nusselt number scaling for heat flux gauge (a) G1 near vane stagnation, (b) G2 near the vane pressure side leading edge, (c) H1 at the passage inlet near midpitch, and (d) H2 near the passage inlet near midpitch
View Large  |  Save Figure  |  Download Slide (.ppt)
Nusselt number scaling for heat flux gauge (a) G1 near vane stagnation, (b) G2 near the vane pressure side leading edge, (c) H1 at the passage inlet near midpitch, and (d) H2 near the passage inlet near midpitch
Figure 9

Nusselt number scaling for heat flux gauge (a) G1 near vane stagnation, (b) G2 near the vane pressure side leading edge, (c) H1 at the passage inlet near midpitch, and (d) H2 near the passage inlet near midpitch

Grahic Jump Location
+Nusselt number scaling for heat flux gauge (a) G3 near the vane pressure side at midaxial chord, (b) H3 near the vane pressure side trailing edge, and (c) H4 near the vane passage exit
View Large  |  Save Figure  |  Download Slide (.ppt)
Nusselt number scaling for heat flux gauge (a) G3 near the vane pressure side at midaxial chord, (b) H3 near the vane pressure side trailing edge, and (c) H4 near the vane passage exit
Figure 10

Nusselt number scaling for heat flux gauge (a) G3 near the vane pressure side at midaxial chord, (b) H3 near the vane pressure side trailing edge, and (c) H4 near the vane passage exit

Grahic Jump Location
+Nusselt number augmentation versus X∕C for each heat flux gauge
View Large  |  Save Figure  |  Download Slide (.ppt)
Nusselt number augmentation versus X∕C for each heat flux gauge
Figure 11

Nusselt number augmentation versus X∕C for each heat flux gauge

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
Outlook
Closed-Cycle Gas Turbines> Chapter 11
Combined Cycle Power Plant
Energy and Power Generation Handbook> Chapter 27
Natural Gas Transmission
Pipeline Design & Construction: A Practical Approach, Third Edition> Chapter 3
Control and Operational Performance
Closed-Cycle Gas Turbines> Chapter 5
Thermodynamic Performance
Closed-Cycle Gas Turbines> Chapter 6
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