Analysis of limitations imposed on one-spool turboprop-engine designs by compressors and turbines at flight mach numbers of 0, 0.6, and 0.8

Cavicchi, Richard H
naca-rm-e56i05
December 06, 1956


Turbine centrifugal stress is a limiting factor for all flight conditions studied. This stress is more severe for sea-level operations than for subsonic flight at the tropopause. Turbines designed for a stress of 30,000 psi are capable of driving a light, compact, high-spedd compressor but only at high values of specific fuel consumption. An increase in turbine-inlet temperature is accompanied by an increase in turbine centrifugal stress. If stresses in excess of 50,000 psi can be tolerated, compressor aerodynamics may become a primary limitation.

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