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Research Papers: Gas Turbines: Heat Transfer

Effect of Simulated Combustor Temperature Nonuniformity on HP Vane and End Wall Heat Transfer: An Experimental and Computational Investigation

[+] Author and Article Information
Imran Qureshi1

Department of Engineering Science, University of Oxford, Parks Road, Oxford OX1 3PJ, UKimran.qureshi@eng.ox.ac.uk

Arrigo Beretta

Turbine Sub-systems, Rolls-Royce PLC, Moor Lane, Derby DE24 8BJ, UK

Thomas Povey

Department of Engineering Science, University of Oxford, Parks Road, Oxford OX1 3PJ, UK

1

Corresponding author.

J. Eng. Gas Turbines Power 133(3), 031901 (Nov 10, 2010) (13 pages) doi:10.1115/1.4002039 History: Received April 29, 2010; Revised May 06, 2010; Published November 10, 2010; Online November 10, 2010

This paper presents experimental measurements and computational predictions of surface and end wall heat transfer for a high-pressure (HP) nozzle guide vane operating as part of a full HP turbine stage in an annular rotating turbine facility, with and without inlet temperature distortion (hot streaks). A detailed aerodynamic survey of the vane surface is also presented. The test turbine was the unshrouded MT1 turbine, installed in the Turbine Test Facility (previously called Isentropic Light Piston Facility) at QinetiQ, Farnborough, UK. This is a short-duration facility, which simulates engine-representative M, Re, nondimensional speed, and gas-to-wall temperature ratio at the turbine inlet. The facility has recently been upgraded to incorporate an advanced second-generation combustor simulator, capable of simulating well-defined, aggressive temperature profiles in both the radial and circumferential directions. This work forms part of the pan-European research program, TATEF II. Measurements of HP vane and end wall heat transfer obtained with inlet temperature distortion are compared with results for uniform inlet conditions. Steady and unsteady computational fluid dynamics (CFD) predictions have also been conducted on vane and end wall surfaces using the Rolls-Royce CFD code HYDRA to complement the analysis of experimental results. The heat transfer measurements presented in this paper are the first of their kind in that the temperature distortion is representative of an extreme cycle point, and was simulated with good periodicity and with well-defined boundary conditions in the test turbine.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic of QinetiQ turbine test facility

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Figure 2

The working section of TTF with the HP turbine stage and turbobrake highlighted

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Figure 3

Turbine inlet total temperature profile: (top) uniform; (bottom) EOTDF

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Figure 4

Circumferentially averaged inlet temperature

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Figure 5

Turbine inlet total pressure profile: (top) uniform; (bottom) EOTDF

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Figure 6

Circumferentially averaged inlet pressure

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Figure 7

NGV isentropic Mach number at 10% span

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Figure 8

NGV isentropic Mach number at 50% span

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Figure 9

NGV isentropic Mach number at 90% span

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Figure 10

Measured NGV Nu for uniform conditions

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Figure 11

Measured NGV normalized Taw at 10% span

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Figure 12

Measured NGV normalized Taw at 50% span

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Figure 13

Measured NGV normalized Taw at 90% span

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Figure 14

Normalized circumferential EOTDF T profiles

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Figure 15

Predicted streamlines on hub wall

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Figure 16

Predicted NGV surface flow streamlines

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Figure 17

Predicted Taw at 10% span

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Figure 18

Predicted Taw at 50% span

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Figure 19

Predicted Taw at 90% span

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Figure 20

CFD prediction of NGV q̇ distribution: (a) uniform; (b) EOTDF

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Figure 21

CFD prediction of HP NGV q̇ distribution: percentage difference between EOTDF and uniform

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Figure 22

CFD prediction of HP NGV h distribution: (top) uniform; (bottom) EOTDF

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Figure 23

CFD prediction of HP NGV Taw distribution: (top) uniform; (bottom) EOTDF

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Figure 24

CFD predicted percentage difference of driving gas temperature between EOTDF and uniform

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Figure 25

Percent change in q̇, Taw−Tw, and h as a function of span, averaged in the chordwise direction over the NGV surface

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Figure 26

Hub end wall Nu: (a) measured uniform, (b) prediction uniform, and (c) prediction EOTDF. Casing end wall Nu: (d) measured uniform, (e) prediction uniform, and (f) prediction EOTDF.

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Figure 27

Casing end wall M: uniform and EOTDF

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Figure 28

Hub end wall M: uniform and EOTDF

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Figure 29

Comparison of predicted heat flux with and without EOTDF: (a) casing end wall; (b) hub end wall

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Figure 30

Comparison of predicted Taw with and without EOTDF: (a) casing end wall; (b) hub end wall

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Figure 31

Comparison of Nu with and without EOTDF: (a) casing end wall; (b) hub end wall

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Figure 32

Change in end wall Nu with the introduction of EOTDF

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Figure 33

Reynolds number based on surface distance

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Figure 34

Effect of freestream temperature on Nusselt number: comparison of analytical model with CFD

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