Saari, Martin J., Prince, William R.
Pressure and temperature distributions throughout an original and a modified 3000-pound-thrust acial-flow turbojet engine are presented for a range of simulated altitudes, simulated flight Mach numbers, and corrected engine speeds. Modification of the original engine improved radial total-pressure distribution at compressor outlet and radial and circumferential temperature distribution at turbine outlet. Pressure and temperature distributions at all measuring stations through the engines, except compressor outlet and turbine outlet, were not appreciably affected by changes in altitude, flight Mach number, or engine speed.
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