RESEARCH PAPERS: Gas Turbines: Heat Transfer

Analyses of Radially Rotating High-Temperature Heat Pipes for Turbomachinery Applications

[+] Author and Article Information
J. Ling, Y. Cao

Department of Mechanical Engineering, Florida International University, Miami, FL 33199

W. S. Chang

Propulsion Directorate, Air Force Research Laboratory, Wright-Patterson AFB, OH 45433

J. Eng. Gas Turbines Power 121(2), 306-312 (Apr 01, 1999) (7 pages) doi:10.1115/1.2817121 History: Received October 20, 1998; Online December 03, 2007


A set of closed-form solutions for the liquid film distributions in the condenser section of a radially rotating miniature heat pipe and for the vapor temperature drop along the heat pipe length are derived. The heat transfer limitations of the heat pipe are analyzed under turbine blade cooling conditions. Analytical results indicate that the condenser heat transfer limitation normally encountered by low-temperature heat pipes no longer exists for the high-temperature rotating heat pipes that are employed for turbine blade cooling. It is found that the heat pipe diameter, radially rotating speed, and operating temperature are very important to the performance of the heat pipe. Heat transfer limitations may be encountered for an increased heat input and rotating speed, or a decreased hydraulic diameter. Based on the extensive analytical evaluations, it is concluded that the radially rotating miniature heat pipe studied in this paper is feasible for turbine blade cooling applications.

Copyright © 1999 by The American Society of Mechanical Engineers
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