A cold air test of an annular nozzle cascade for a transonic axial-flow turbine was made in a cascade exit flow Mach number ranging from 0.2 to 1.2. The tip diameter, the hub diameter, the maximum blade thickness ratio at the mean and the trailing edge thickness are 512.9 mm, 355.0 mm, 12.4% and 0.2 mm respectively, and the nozzle exit flow Mach number at the design point is 1.322 at the nozzle hub. In order to prevent the flow from separation which may occur in adverse pressure regions on the blade surface, a low diffusion parameter blade was designed and used for the cascade. Comparing this with the previous test results of an annular turbine nozzle cascade using a T-6 profile, a great improvement was seen in aerodynamic characteristics. The test result showed good agreement with the results of a two-dimensional cascade test. (Author)
An Investigation of a Transonic Axial-Flow Turbine. 1 a Cold Air Test of the Annular Turbine Nozzle Cascade
1972
16 pages
Report
Keine Angabe
Englisch
High speed annular cascade wind tunnel and transonic axial flow test compressor
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