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.

Copyright © 2010 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Figure 1

Typical sections of a turbine blade (1)

Grahic Jump Location
Figure 2

Schematic of experimental setup (not to scale)

Grahic Jump Location
Figure 3

Detailed description of working section geometry

Grahic Jump Location
Figure 4

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

Grahic Jump Location
Figure 5

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

Grahic Jump Location
Figure 6

Passage htc results using narrower scale for better understanding of results

Grahic Jump Location
Figure 7

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

Grahic Jump Location
Figure 8

CFD path lines colored by the x-axis velocity

Grahic Jump Location
Figure 9

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

Grahic Jump Location
Figure 10

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

Grahic Jump Location
Figure 11

In-hole htc distribution, Reinlet=69,959

Grahic Jump Location
Figure 12

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

Grahic Jump Location
Figure 13

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

Grahic Jump Location
Figure 14

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




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In