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Combustion Gas Turbine for Airplanes


Lancaster, Otis Ewing (1945) Combustion Gas Turbine for Airplanes. Engineer's thesis, California Institute of Technology. doi:10.7907/82FF-C054.


This paper contains a theoretical study of various thermodynamic cycles for Gas-Turbine-propeller propulsion units for aircraft. The object of the study was to evaluate the turbine-propeller engines as a source of power for fast, economical, long range airplanes. Hence, the consumption of fuel and the total weight of fuel and power plant were the main criterion for the evaluation. Since the weights of the particular units were not known, most of the results here are centered around the fuel consumption per horsepower, emphasizing the design criteria and throttle conditions for minimum values. In order to emphasize the maximum possible performance, formulae for ideal engines were developed for all cases. These relations are compared with the corresponding ones involving unknown efficiencies. A summary table of these comparison formulae is given at the close of the thesis. In the case of the cycles where there was sufficient experimental data available to estimate the performance of the component parts, the relations for power and specific fuel consumption were written in terms of three parameters which were convenient for graphical use in design purposes.

Item Type:Thesis (Engineer's thesis)
Subject Keywords:(Aeronautical Engineering)
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Unknown, Unknown
Thesis Committee:
  • Unknown, Unknown
Defense Date:1945
Record Number:CaltechETD:etd-11242008-110400
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4654
Deposited By: Imported from ETD-db
Deposited On:11 Dec 2008
Last Modified:10 Nov 2023 19:51

Thesis Files

PDF (Lancaster_oe_1945.pdf) - Final Version
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