22 research outputs found
Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine. II - Performance of Inlet Guide Vanes as Separate Component
The inlet wide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached. The total-pressure loss through the guide vanes was approximately 1 percent for the unchoked conditions and from 5 to 6 percent when choked
Investigation of a Supersonic-compressor Rotor with Turning to Axial Direction II : Rotor Component Off-design and Stage Performance
Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 III : blade-element and over-all performance at three solidity levels
Experimental Investigation of a 16-inch Impulse-type Supersonic-compressor Rotor
Performance data and characteristics of a 16-inch impulse-type supersonic-compressor rotor are presented. The experimental portion of this investigation was conducted in Freon-12. A peak pressure ratio of 3.6 was obtained with an adiabatic efficiency of 0.80 at design conditions. Performance was continuous from impulse operation, at open throttle, to shock-in-rotor operation at the stall condition
Investigation of a Supersonic-compressor Rotor with Turning to Axial Direction I : Rotor Design and Performance
Experimental Investigation of a Transonic Compressor Rotor with a 1.5-inch Chord Length and an Aspect Ratio of 3.0 I : Design, Over-all Performance, and Rotating-stall Characteristics
Recommended from our members
NACA Research Memorandums
"The inlet guide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached" (p. 1)