0
Research Papers

Heat Transfer in Leading Edge, Triangular Shaped Cooling Channels With Angled Ribs Under High Rotation Numbers

[+] Author and Article Information
Yao-Hsien Liu, Michael Huh

Turbine Heat Transfer Laboratory, Texas A&M University, College Station, TX 77843-3123

Dong-Ho Rhee

 Korea Aerospace Research Institute, Daejeon 305-333, Korea

Je-Chin Han

Turbine Heat Transfer Laboratory, Texas A&M University, College Station, TX 77843-3123jc-han@tamu.edu

Hee-Koo Moon

 Solar Turbines Inc., San Diego, CA 92186

J. Turbomach 131(4), 041017 (Jul 09, 2009) (12 pages) doi:10.1115/1.3072493 History: Received August 29, 2008; Revised September 21, 2008; Published July 09, 2009

The gas turbine blade/vane internal cooling is achieved by circulating compressed air through the cooling channels inside the turbine blade. Cooling channel geometries vary to fit the blade profile. This paper experimentally investigated the rotational effects on heat transfer in an equilateral triangular channel (Dh=1.83cm). The triangular shaped channel is applicable to the leading edge of the gas turbine blade. Angled 45 deg ribs are placed on the leading and trailing surfaces of the test section to enhance heat transfer. The rib pitch-to-rib height ratio (P/e) is 8 and the rib height-to-channel hydraulic diameter ratio (e/Dh) is 0.087. Effect of the angled ribs under high rotation numbers and buoyancy parameters is also presented. Results show that due to the radially outward flow, heat transfer is enhanced with rotation on the trailing surface. By varying the Reynolds numbers (10,000–40,000) and the rotational speeds (0–400 rpm), the rotation number and buoyancy parameter reached in this study are 0–0.58 and 0–1.9, respectively. The higher rotation number and buoyancy parameter correlate very well and can be used to predict the rotational heat transfer in the equilateral triangular channel.

FIGURES IN THIS ARTICLE
<>
Copyright © 2009 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Internal gas turbine blade cooling passage

Grahic Jump Location
Figure 2

Rotating facility with the test section

Grahic Jump Location
Figure 3

(a) Details of the triangular test section and (b) cross section view of the test section

Grahic Jump Location
Figure 4

Rib configurations of the current study

Grahic Jump Location
Figure 5

Conceptual view of the secondary flow due to rotation and ribs

Grahic Jump Location
Figure 6

Nusselt number ratio (Nu/Nuo) comparison in the stationary channel (Re=20,000)

Grahic Jump Location
Figure 7

Nusselt number ratios (Nus/Nuo) in the stationary channel

Grahic Jump Location
Figure 8

Nusselt number ratios (Nu/Nuo) in a smooth channel

Grahic Jump Location
Figure 9

Nusselt number ratios (Nu/Nuo) in a ribbed channel

Grahic Jump Location
Figure 10

Effect of rotation number on three different regions

Grahic Jump Location
Figure 11

Effect of buoyancy parameter on three different regions

Grahic Jump Location
Figure 12

Streamwise averaged Nusselt number ratio (Nu/Nus) with rotation number

Grahic Jump Location
Figure 13

Streamwise averaged Nusselt number ratio (Nu/Nus) comparison with buoyancy parameter

Grahic Jump Location
Figure 14

Average Nu ratio (Nu/Nus) for the leading and trailing surfaces and the correlation

Tables

Errata

Discussions

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