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An Experimental Singlestage Aircooled Turbine

An Experimental Singlestage Aircooled Turbine A comprehensive series of tests have been made on an experimental singlestage turbine to determine the cooling characteristics and the overall stage performance of a set of aircooled turbine blades. These blades, which arc described fully in Part I of this paper had, internally, a multiplicity of passages of small diameter along which cool air was passed through the whole length of the blade. Analysis of the test data indicated that, when a quantity of cooling air amounting to 2 per cent, by weight, of the total gasflow through the turbine is fed to the row of rotor blades, an increase in gas temperature of about 270 dcg. C. 518 deg. F. should be permissible above the maximum allowable value for a row of uncoolcd blades made from the same material. The degree of cooling achieved throughout each blade was far from uniform and large thermal stresses must result. It appears, however, that the consequences of this are not highly detrimental to the performance of the present type of blading, it being demonstrated that the main effect of the induced thermal stress isapparently to transfer the major tensile stresses to the cooler and hence stronger regions of the blade. The results obtained from the present investigations do not represent a limit to the potentialities of internal aircooling, but form merely a first exploratory step. At the same time the practical feasibility of air cooling is made apparent, and advances up to the present arc undoubtedly encouraging. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

An Experimental Singlestage Aircooled Turbine

Ainley, D.G.
Aircraft Engineering and Aerospace Technology , Volume 25 (9): 8 – Sep 1, 1953
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032333
Publisher site
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Abstract

A comprehensive series of tests have been made on an experimental singlestage turbine to determine the cooling characteristics and the overall stage performance of a set of aircooled turbine blades. These blades, which arc described fully in Part I of this paper had, internally, a multiplicity of passages of small diameter along which cool air was passed through the whole length of the blade. Analysis of the test data indicated that, when a quantity of cooling air amounting to 2 per cent, by weight, of the total gasflow through the turbine is fed to the row of rotor blades, an increase in gas temperature of about 270 dcg. C. 518 deg. F. should be permissible above the maximum allowable value for a row of uncoolcd blades made from the same material. The degree of cooling achieved throughout each blade was far from uniform and large thermal stresses must result. It appears, however, that the consequences of this are not highly detrimental to the performance of the present type of blading, it being demonstrated that the main effect of the induced thermal stress isapparently to transfer the major tensile stresses to the cooler and hence stronger regions of the blade. The results obtained from the present investigations do not represent a limit to the potentialities of internal aircooling, but form merely a first exploratory step. At the same time the practical feasibility of air cooling is made apparent, and advances up to the present arc undoubtedly encouraging.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Sep 1, 1953

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