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
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.

An Adobe Acrobat (PDF) file of the entire report: