Experimental study of a high-through-flow transonic axial compressor stage

Journal Article · Sun Jul 01 00:00:00 EDT 1984 · J. Eng. Gas Turb.; (United States)

DOI:https://doi.org/10.1115/1.3239606· OSTI ID:6081340

Wennerstorm, A J

Design information and experimental results are presented for a transonic axial compressor stage passing 40 lbs/s-ft/sup 2/ frontal area (195 Kg/s-m/sup 2/) with a pressure ratio of 1.95 at 1500 ft/s (457 m/s) tip speed. The design incorporates several unusual features that helped it achieve a peak isentropic efficiency over 88 percent at design speed. The compressor was evaluated at three rotor tip clearances and an optimum was found. Vortex generators placed upstream on the casing proved relatively ineffective in influencing stall margin. Vortex generators installed on the rotor did improve stall margin and also increased efficiency at speeds of 90 percent and below.

• Research Organization: Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson AFB, Ohio
• OSTI ID: 6081340
• Journal Information: J. Eng. Gas Turb.; (United States), Vol. 106:3
• Country of Publication: United States
• Language: English

Related Subjects

20 FOSSIL-FUELED POWER PLANTS
GAS COMPRESSORS
DESIGN
FINS
MECHANICAL EFFICIENCY
OPERATION
OPTIMIZATION
PERFORMANCE TESTING
ROTORS
TRANSONIC FLOW
VELOCITY
VORTEX FLOW
COMPRESSORS
EFFICIENCY
FLUID FLOW
TESTING
200104* - Fossil-Fueled Power Plants- Components