Analytical Performance Study of Turbojet Cycle with Nearly Ideal Component Efficiencies

Author: Hughes, Richard Frank

Year: 1951

Degree: Engineer's thesis

Advisor: Marble, Frank E.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/Q2CP-J309

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?

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