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Performance of tandem-bladed transonic compressor rotor with tip speed of 1375 feet per secondThe design and experimental performance of a 20-inch diameter tandem-bladed axial-flow transonic compressor rotor is presented. Radial surveys were made of the flow conditions. At design speed the peak efficiency was 0.88 and occurred at an equivalent weight flow of 63 pounds per second. At peak efficiency the total pressure and total temperature ratios were 1.77 and 1.20, respectively. The stall margin at design speed was 10 percent based on weight flows and total pressure ratios at peak efficiency and near stall.
Document ID
19720011123
Document Type
Technical Memorandum (TM)
Authors
Urasek, D. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Janetzke, D. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-2484
E-6388
Funding Number(s)
PROJECT: RTOP 764-74
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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