二次元軸流タービン翼列の拡散係数による負荷限界予測

概要

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The present paper is an attempt to estimate plane turbine cascade loading limit using the loss parameter. Experimental measurements in the low-speed cascade How of a low-pressure turbine rotor and stator blade profile which were used in a gas turbine engine are presented. Cascade tests were performed for the pitch ratio of 0.54〜0.89 and incidence angle of -30〜+27.5°at the center of the blade span. The test results obtained are compared with the one using the Ainley-Mathieson method, at the design point of the engine. A good correlation between diffusion factor and loss parameter and loading limit can be obtained through the data in this paper and the previously contributed one with hub, mean and tip section of the blade profile.
一般社団法人日本機械学会の論文
1994-09-25