John J. Rebeske, Jr., James F. Dugan, Jr.
Component performance data for one modification of a 16-stage compressor and a 3-stage turbine were used to determine the matched performance characteristics of an engine having these components. The turbine power-limit line and equilibrium operating lines for exhaust-nozzle areas of 360, 395, 420, 600, and infinite square inches were determined. Matched performance characteristics were determine for leakages of 0, 2, and 5.5 percent. Operation in the surge region was investigated for one available experimental point.
An Adobe Acrobat (PDF) file of the entire report: