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Effect of Stator and Rotor Aspect Ratio on Transonic-Turbine PerformanceThe effect of stator and rotor aspect ratio on transonic-turbine performance was experimentally investigated. The stator aspect ratios covered were 1.6. 0.8, and 0.4, while the rotor aspect ratios investigated were 1.46 and 0.73. It was found that the observed variation in turbine design-point efficiency was negligible. Thus, within the range of aspect ratio investigated, these results verify for turbines operating in the transonic flow range the finding of a reference report, which showed analytically that, if blade shape and solidity are held constant, the aspect ratio may be varied over a wide range without appreciable change in turbine efficiency.
Document ID
19980228409
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Wong, Robert Y. (NASA Lewis Research Center Cleveland, OH United States)
Monroe, Daniel E. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1959
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-MEMO-2-11-59E
E-177
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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