Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed IV : effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed

Elmer H. Davison, Robert E. English
naca-rm-e52h13
Nov 1952


The range of application of two-stage turbines to driving single-spool compressors was studied by investigating the turbine blade-tip speeds required in order that satisfactory two-stage turbines can be designed to drive a particular compressor over a range of engine operation at rated rotative speed. The relatively low blade-tip speed, high work, and high air flow per unit frontal area of this compressor make critical the problem of designing such a two-stage turbine.

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