A Small Axial-Centrifugal Compressor Matching Study Program
Final rept. 1 Jun-31 Dec 1969
AIRESEARCH MFG CO OF ARIZONA PHOENIX
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Engine cycle studies in which compressor component performance anticipated in 1973 was used were conducted to select operating conditions for a 3-pound-per-second front-drive gas turbine optimized for minimum specific fuel consumption SFC at 60-percent power. Fixed turbine geometry was assumed. Preliminary matching studies of seven combinations of axial and centrifugal compressor stages were conducted to accomplish cycle requirements for 20-, 30-, 60, and 100-percent-power operation. The compressor type selected--two axial stages employing variable inlet guide vanes plus one centrifugal stage--was configured in a preliminary design for application in a preliminary engine layout.
- Jet and Gas Turbine Engines