Experimental evaluation and modeling of a turbine blade with potassium evaporative cooling

A new method of turbine blade cooling, the Return Flow Cascade, has been developed in which vaporization of a liquid metal such as potassium is used to maintain the blade surface at a nearly uniform temperature. Turbine blades cooled using this technology have lower blade temperature levels compared to that available with conventional air cooling, potentially resulting in higher firing temperatures or a choice of a wider range of materials for the hot gas path. The detailed operation of the Return Flow Cascade is described including fluid mechanic and heat transfer phenomena that occur at high heat flux and gravitational acceleration levels characteristic of modern gas turbine engines. The performance limits of the Return Flow Cascade are identified by the development of a theoretical model that estimates the performance of the system for a range of operating conditions found in the experimental test rig and in an actual gas turbine engine. These limits include vapor choking in the internal blade passages, pool boiling limits in the blade, and surface tension restriction of liquid flow. Experimental results are presented from testing in the Rotating Heat Transfer Rig at the Massachusetts Institute of Technology. An infrared detector capable of high scan rates was used to fully map the temperature distribution of a single, heated, rotating turbine blade. The blade surface temperature maps show that the Return Flow Cascade works as designed by enforcing a nearly constant temperature over the surface of the blade. Cascade initiation limits predicted by the internal vapor choking model are in good agreement with the test data.

Department dc:contributor.department

Massachusetts Institute of Technology. Department of Aeronautics and Astronautics

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2004

Author dc:creator

• Townsend, Jessica Lee

Advisor dc:contributor.advisor

• Jack L. Kerrebrock.

• Aeronautics and Astronautics.

Statement dc:rights

• M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.

Licence dc:rights.uri

• http://dspace.mit.edu/handle/1721.1/7582

Language dc:language.iso

eng

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/17831

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/17831