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Research turbine for high-temperature core engine application. 2: Effect of rotor tip clearance on overall performance (1974)

Behning, F. P. ; Schum, H. J. ; Szanca, E. M.

In: CASI

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Publication Date: 2019-06-27

Description: A 25.4-cm (10-in) tip diameter turbine was tested to determine the effect of rotor radial tip clearance on turbine overall performance. The test turbine was a half-scale model of a 50.8-cm-(20-in.-) diameter research turbine designed for high-temperature core engine application. The test turbine was fabricated with solid vanes and blades with no provision for cooling air and tested at much reduced inlet conditions. The tests were run at design speed over a range of pressure ratios for three different rotor clearances ranging from 2.3 to 6.7 percent of the annular blade passage height. The results obtained are compared to the results obtained with three other turbines of varying amounts of reaction.

Keywords: AERODYNAMICS

Type: NASA-TN-D-7639 , E-7728

Format: application/pdf

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