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Research Papers

Detailed Heat Transfer Measurements in a Model of an Integrally Cast Cooling Passage

[+] Author and Article Information
Ioannis Ieronymidis

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

David R. H. Gillespie

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

Peter T. Ireland

 Rolls-Royce plc., P.O. Box 3, Filton, Bristol BS34 7QE, UK

Robert Kingston

 Rolls-Royce plc., P.O. Box 3, Filton, Bristol BS34 7QE, UKrobert.kingston@rolls-royce.com

J. Turbomach 132(2), 021002 (Dec 31, 2009) (9 pages) doi:10.1115/1.3140283 History: Received June 09, 2006; Revised June 21, 2006; Published December 31, 2009; Online December 31, 2009

Detailed measurements of the heat transfer coefficient (htc) distributions on the internal surfaces of a novel gas turbine blade cooling configuration were carried out using a transient liquid crystal technique. The cooling geometry, in which a series of racetrack passages are connected to a central plenum, provides high heat transfer coefficients in regions of the blade in good thermal contact with the outer blade surface. The Reynolds number changes along its length because of the ejection of fluid through a series of 19 transfer holes in a staggered arrangement, which are used to connect ceramic cores during the casting process. Heat transfer coefficient distributions on these holes surface are particularly important in the prediction of blade life, as are heat transfer coefficients within the hole. The results at passage inlet Reynolds numbers of 21,667, 45,596, and 69,959 are presented along with in-hole htc distributions at Rehole=5930, 12,479, 19,147; and suction ratios of 0.98, 1.31, 2.08, and 18.67, respectively. All values are engine representative. Characteristic regions of high heat transfer downstream of the transfer holes were observed with enhancement of up to 92% over the Dittus–Boelter level. Within the transfer holes, the average htc level was strongly affected by the cross-flow at the hole entrance. htc levels were low in these short (l/d=1.5) holes fed from regions of developed boundary layer.

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Figures

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Figure 1

Typical sections of a turbine blade (1)

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Figure 2

Schematic of experimental setup (not to scale)

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Figure 3

Detailed description of working section geometry

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Figure 4

Typical pressure and mass flow rate distributions within the passage, Reinlet=45,596

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Figure 5

Camera view and lighting arrangement for passage htc experiments (not to scale)

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Figure 6

Passage htc results using narrower scale for better understanding of results

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Figure 7

CFD path lines released from a surface along the passage centerline (x/d=0) showing flow oscillations

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Figure 8

CFD path lines colored by the x-axis velocity

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Figure 9

Average experimental htc and Dittus–Boelter correlation for surfaces between holes

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Figure 10

Camera and lighting arrangement for in-hole htc experiments (not to scale)

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Figure 11

In-hole htc distribution, Reinlet=69,959

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Figure 12

In-hole angle notation and path lines close to the surface of the hole colored by the z-axis velocity

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Figure 13

Circumferentially averaged in-hole htc for same hole and different Reinlet

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Figure 14

Circumferentially averaged in-hole htc for same Reinlet and different hole

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