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Research Papers

Stagnation Region Heat Transfer Augmentation at Very High Turbulence Levels

[+] Author and Article Information
J. E. Kingery

Raytheon Missile Systems,
1151 E. Hermans Road,
Tucson, AZ 85756
e-mail: kingery.joseph@gmail.com

F. E. Ames

Mechanical Engineering Department,
University of North Dakota,
Grand Forks, ND 58202
e-mail: forrest.ames@engr.und.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received December 14, 2015; final manuscript received January 19, 2016; published online March 22, 2016. Editor: Kenneth C. Hall.The United States Government retains, and by accepting the article for publication, the publisher acknowledges that the United States Government retains, a nonexclusive, paid-up, irrevocable, worldwide license to publish or reproduce the published form of this work, or allow others to do so, for United States government purposes.

J. Turbomach 138(8), 081005 (Mar 22, 2016) (10 pages) Paper No: TURBO-15-1303; doi: 10.1115/1.4032677 History: Received December 14, 2015; Revised January 19, 2016

Current land-based gas turbines are growing in size producing higher approach flow Reynolds numbers at the leading edge of turbine nozzles. These vanes are subjected to high intensity large scale turbulence. This present paper reports on the research which significantly expands the parameter range for stagnation region heat transfer augmentation due to high intensity turbulence. Heat transfer measurements were acquired over two constant heat flux test surfaces with large diameter leading edges (10.16 cm and 40.64 cm). The test surfaces were placed downstream from a new high intensity (17.4%) mock combustor and tested over an eight to one range in approach flow Reynolds number for each test surface. Stagnation region heat transfer augmentation for the smaller (ReD = 15,625–125,000) and larger (ReD = 62,500–500,000) leading edge regions ranged from 45% to 81% and 80% to 136%, respectively. These data also include heat transfer distributions over the full test surface compared with the earlier data acquired at six additional inlet turbulence conditions. These surfaces exhibit continued but more moderate acceleration downstream from the stagnation regions and these data are expected to be useful in testing bypass transition predictive approaches. This database will be useful to gas turbine heat transfer design engineers.

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Figures

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Fig. 1

Wind tunnel facility used for stagnation heat transfer experiments

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Fig. 2

Photo of large cylindrical leading edge heat transfer surface installed in UND's wind tunnel facility

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Fig. 3

Schematic of original aero-combustor turbulence generator cross section showing back panel slots for wall jets and side panel plunged holes for primary and dilution holes

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Fig. 4

Comparison of the initial and the redesigned very high turbulence aero-combustor simulators

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Fig. 5

Cross-span velocity distributions at various distances downstream from new very high turbulence generator

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Fig. 6

One-dimensional power spectra of u’ showing two streamwise and three spanwise locations for 10 m/s

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Fig. 7

Half profiles of smaller and larger cylindrical leading edge test surfaces with top wall

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Fig. 8

Surface velocity distribution for smaller and larger leading edge test surfaces downstream from stagnation line

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Fig. 9

Acceleration distributions for smaller and larger cylindrical leading edge test surfaces from stagnation line

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Fig. 10

Expanded stagnation heat transfer results with very high turbulence generator (AH)

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Fig. 11

Correlation of absolute augmentation level with dissipation as a function of Reynolds number over diameter

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Fig. 12

Effects of turbulence on smaller leading edge test surface heat transfer, ReD = 31,250

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Fig. 13

Effects of turbulence on smaller leading edge test surface heat transfer, ReD = 62,500

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Fig. 14

Effects of turbulence on smaller leading edge test surface heat transfer, ReD = 125,000

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Fig. 15

Effects of turbulence on larger leading edge test surface heat transfer, ReD = 125,000

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Fig. 16

Effects of turbulence on larger leading edge test surface heat transfer, ReD = 250,000

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Fig. 17

Effects of turbulence on larger leading edge test surface heat transfer, ReD = 500,000

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