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Research Papers

Experimental and Numerical Analysis of Gas Turbine Blades With Different Internal Cooling Geometries

[+] Author and Article Information
M. Eifel

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen University, Aachen, NRW 52062, Germanyeifel@ist.rwth-aachen.de

V. Caspary

 MAN Turbo AG, Steinbrinkstrasse 1, Oberhausen, NRW 46145, Germanyvolker.caspary@man.eu

H. Hönen

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen University, Aachen, NRW 52062, Germany

P. Jeschke

Institute of Jet Propulsion and Turbomachinery, RWTH Aachen University, Aachen, NRW 52062, Germanyjeschke@ist.rwth-aachen.de

J. Turbomach 133(1), 011018 (Sep 23, 2010) (9 pages) doi:10.1115/1.4000541 History: Received July 02, 2009; Revised July 27, 2009; Published September 23, 2010; Online September 23, 2010

This paper presents the effects of major geometrical modifications to the interior of a convection cooled gas turbine rotor blade. The analysis of the flow is performed experimentally with flow visualization via paint injection into water, whereas the flow and the heat transfer are investigated numerically with ANSYS CFX , utilizing the SST turbulence model. Two sets of calculations are carried out: one under the same conditions as the experiments and another according to realistic hot gas conditions with conjugate heat transfer. The aim is to identify flow phenomena altering the heat transfer in the blade and to manipulate them in order to reduce the thermal load of the material. The operating point of the geometric base configuration is set to Re=50,000 at the inlet while for the modified geometries, the pressure ratio is held constant compared with the base. Flow structures and heat transfer conditions are evaluated and are linked to specific geometric features. Among several investigated configurations one could be identified that leads to a cooling effectiveness 15% larger compared with the base.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

Test section in basin with inlet channel

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Figure 3

Test section (base configuration) close-up

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Figure 4

Vortex after 180 deg bend (base); view from below

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Figure 5

Vortex at rear inlet (base); side view

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Figure 6

Vortex ahead of pin fin array (base); side view

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Figure 7

Tetrahedral mesh with prism layers

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Figure 8

Hexahedral mesh with O-grid

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Figure 9

Flow pattern (base)

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Figure 10

Cutting planes for vortex structure visualization (red) and temperature difference calculation (blue)

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Figure 11

Rib induced vortices (base)

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Figure 12

Rib induced vortices (variation A)

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Figure 18

Temperature gradients in cutting planes at 6%, 50%, and 94% height (variation A)

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Figure 1

Five geometry configurations; variation D duplicates the base configuration without tip holes and is not shown

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Figure 13

Rib/dimple induced vortices (variation B)

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Figure 14

Flow after breakthroughs (variation C)

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Figure 15

External flow (midplane)

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Figure 16

Cutting planes at 6%, 50%, and 94% height

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Figure 17

Temperature distribution on blade surface (base)

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Figure 19

Temperature gradients in cutting planes at 6%, 50%, and 94% height (variation B)

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Figure 20

Temperature gradients in cutting planes at 6%, 50%, and 94% height (variation C)

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Figure 21

Temperature distribution on blade surface (variation D)

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