GLTRS--Glenn
TITLE AND SUBTITLE:
Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped With a Mean-Camberline Strip

AUTHOR(S):
A.A. Ameri

REPORT DATE:
May 2001

FUNDING NUMBERS:
WU-714-03-50-00
NAS3-00180

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
AYT Corporation
2001 Aerospace Parkway
Brook Park, Ohio 44142

PERFORMING ORGANIZATION REPORT NUMBER:
E-12693

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Final Contractor Report

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA CR-2001-210764
2001-GT-0156

SUPPLEMENTARY NOTES:
Prepared for the 2001 Summer Annual Gas Turbine Conference sponsored by the American Society of Mechanical Engineers, New Orleans, Louisiana, June 3-7, 2001. Project Manager, R. Gaugler, Turbomachinery and Propulsion Systems Division, NASA Glenn Research Center, organization code 5820, 216-433-5882.

ABSTRACT:
Experimental and computational studies have been performed to investigate the detailed distribution of convective
heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (>100 MW). In a previous work the numerical heat transfer results for a sharp edge blade tip and a radiused blade tip were presented. More recently several other tip treatments have been considered for which the tip heat transfer has been measured and documented. This paper is concerned with the numerical prediction of the tip surface heat transfer for radiused blade tip equipped with mean-camberline strip (or "squealer" as it is often called). The heat transfer results are compared with the experimental results and discussed. The effectiveness of the mean-camberline strip in reducing the tip leakage and the tip heat transfer as compared to a radiused edge tip and sharp edge tip was studied. The calculations show that the sharp edge tip works best (among the cases considered) in reducing the tip leakage flow and the tip heat transfer.

SUBJECT TERMS:
Turbomachinery; Gas turbine; Turbine heat transfer; Modeling; Blade Tip

NUMBER OF PAGES:
12

PDF AVAILABLE FROM URL:
2001/CR-2001-210764.pdf
( 2,464 KB )

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