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- W2063670403 abstract "The axial supersonic compressors of the “shock-in-rotor” type are under development for application to small gas turbines. A passage flow approach and passage criteria were used to design and develop the airfoils for the highly loaded rotor and stator blading of these 4 lb/sec machines. The overall stage performance values demonstrated to date are 2.06:1 pressure ratio at 78 percent adiabatic efficiency and 2.56:1 at 74.4 percent efficiency. The loss data and static pressure rise measured for the rotors and exit stators provide ample evidence that the higher design performance goals can be met." @default.
- W2063670403 created "2016-06-24" @default.
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- W2063670403 date "1969-03-09" @default.
- W2063670403 modified "2023-10-16" @default.
- W2063670403 title "The Development of Supersonic Axial Compressor Boost Stages for Small Gas Turbines" @default.
- W2063670403 doi "https://doi.org/10.1115/69-gt-44" @default.
- W2063670403 hasPublicationYear "1969" @default.
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