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Research Papers

Film Cooling in a Separated Flow Field on a Novel Lightweight Turbine Blade

[+] Author and Article Information
Yoji Okita, Chiyuki Nakamata

Aero-Engine and Space Operations, IHI Corporation, Tokyo 190-1297, Japan

Masaya Kumada

Department of Mechanical Engineering, Gifu University, Gifu 501-1193, Japan

Masahiro Ikeda

Institute of Industrial Science, University of Tokyo, Tokyo 153-8505, Japan

J. Turbomach 132(3), 031003 (Mar 24, 2010) (12 pages) doi:10.1115/1.3144165 History: Received July 14, 2008; Revised March 09, 2009; Published March 24, 2010; Online March 24, 2010

The primary contribution of this research is to clarify the feasibility of a novel lightweight turbine blade with internal and external cooling, which is invented, aiming at drastic reduction in weight. With a considerably thinner airfoil, an extensive separation bubble is formed on the pressure side, and film cooling performance in such a flow field has to be investigated. Experimental results with a curved duct setup, which simulates the flow field around the proposed airfoil, show that a film cooling is still an effective measure of cooling even in the vastly separated region, and it behaves quite similarly to the conventional correlation, except for lower blowing ratios, where the thermal field is strongly affected by the intense recirculation flow. Comparisons between the experimental and numerical results verify that an affordable Reynolds-averaged Navier–Stokes simulation is useful to investigate the detailed physics of this flow field. With the numerical modeling, a cooling performance of the proposed blade under a typical engine operating condition is simulated, and the metal temperatures of the blade are also predicted with a fluid-solid conjugate calculation. The resultant thermal distribution in the airfoil suggests that the trailing edge portion is inevitably most critical in the temperature, and also a considerable thermal gradient across the blade is induced. Thermal profile, however, is partly recovered with some of the film coolant being bypassed from the pressure side to the suction side.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Sketch of the lightweight cooled blade

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Figure 2

General arrangement of the facility

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Figure 3

Schematic of the curved duct test section

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Figure 4

Thermocouple locations for the fluid temperature traverse

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Figure 5

Computational domain and mesh

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Figure 6

Comparison of streamwise distribution of calculated film effectiveness with the two grids for M=1.0

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Figure 7

Comparison of static pressure coefficient between the curved duct and the blade passage (numerical results)

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Figure 8

Streamwise distribution of the measured centerline film effectiveness with different blowing ratios

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Figure 9

Comparison of the streamwise profile of film effectiveness between the present data and the correlation by Taslim (3)

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Figure 10

Comparison of streamwise distribution of the centerline film effectiveness with different blowing ratios

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Figure 11

Measured contours of the spatial thermal field (θ) in the duct with different blowing ratios

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Figure 12

Predicted contours of the spatial thermal field (θ) in the duct with different blowing ratios

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Figure 13

Calculated velocity vectors near the film coolant injection

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Figure 14

Computational domain and mesh around the lightweight blade

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Figure 15

Comparison of streamwise distribution of calculated film effectiveness with the two grids for M=1.0

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Figure 16

Computed isentropic surface Mach number profiles with the conventional and the lightweight airfoils

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Figure 17

Pitchwise distribution of computed loss coefficient with the conventional and the lightweight airfoils

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Figure 18

Heat transfer coefficient on the pressure surface with the conventional and the lightweight airfoils

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Figure 19

Comparison of streamwise distribution of calculated film effectiveness with different blowing ratios

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Figure 20

Predicted contours of temperature (θ) around the lightweight blade with different blowing ratios

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Figure 21

Predicted contours of fluid and solid temperature (θ) with pressure-side and suction-side film cooling (M=2.0 for pressure-side blowing)

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Figure 22

Predicted contours of fluid and solid temperature (θ) with two different bypass hole locations (M=2.0 for pressure-side blowing and M=1.0 for suction-side)

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