Supersonic Through-Flow Fan Design

Steinke National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 Abstract The NASA Lewis Research Center has embarked on a program to experimentally prove the concept of a supersonic through-flow fan which is to maintain supersonic velocities throughout the compression system with only weak shock-wave flow losses. This paper describes the detailed design of a supersonic through-flow fan and estimated off-design perform- ance with the use of advanced computational codes. A multistage compressor facility is being modified for the newly designed supersonic through-flow fan and the major aspects of this modification are briefly described. Introduction The current desire to fly passengers across the Pacific Ocean at supersonic speeds of Mach 3 or greater1 has created interest in developing better power plants to sustain efficient supersonic cruise flight. At subsonic speeds, the turbofan engine has the thrust potential needed for take off and climb and is more efficient and quieter than