圧縮機用翼型の一翼列実験

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タイトル別名
  • Some Tests on Cascades of a Compressor Blade
  • アッシュクキヨウヨクガタ ノ イチヨクレツ ジッケン

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説明

Cascade tests were made on a compressor blade with a prescribed pressure distribution. (i) In the tests of cascades of compressor blades, there exists enormous increase in the axial velocity through cascades caused by the growth of boundary layer on both side walls, and the test results deviate considerably from what the two-dimensional potential theory predicts. (ii) In order to estimate the effects of increase in the axial velocity through cascades, a simple two-dimensional model with sources as show in Fig.12 is assumed to represent the actual status, and a calculation is carried out about it. A comparison with experimental results leads to a satisfactory agreement in regard to turning angle and pressure distribution. (iii) The method presented here is considered to afford a correction which deduces two-dimensional characteristics of blades in cascades from data obtained in conventional cascade tunnels, however, further examination with data from various test facilities will be needed.

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