Analytical Performance Study of Turbojet Cycle with Nearly Ideal Component Efficiencies

Citation

Hughes, Richard Frank (1951) Analytical Performance Study of Turbojet Cycle with Nearly Ideal Component Efficiencies. Engineer's thesis, California Institute of Technology. doi:10.7907/Q2CP-J309. https://resolver.caltech.edu/CaltechETD:etd-03192009-161901

Abstract

The performance of the turbojet engine for high component efficiency is approximated by an ideal expression (efficiencies equal unity) plus the first terms of a Taylor Series expansion for the purpose of isolating the individual effects of the components. The analytical solution to two optimizations is presented; namely: (A) For fixed burner outlet temperature, flight Mach number, and component efficiency, what is the compressor pressure ratio corresponding to maximum jet velocity (maximum thrust per unit mass flow)? (B) For fixed flight Mach number, compressor pressure ratio and component efficiency, what is the burner outlet temperature corresponding to minimum specific fuel consumption?

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):	Marble, Frank E.
Group:	GALCIT
Thesis Committee:	Unknown, Unknown
Defense Date:	1 January 1951
Record Number:	CaltechETD:etd-03192009-161901
Persistent URL:	https://resolver.caltech.edu/CaltechETD:etd-03192009-161901
DOI:	10.7907/Q2CP-J309
Default Usage Policy:	No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:	1031
Collection:	CaltechTHESIS
Deposited By:	Imported from ETD-db
Deposited On:	23 Mar 2009
Last Modified:	03 May 2023 19:18

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