Hughes, Richard F. (1951) Analytical performance study of turbojet cycle with nearly ideal component efficiencies. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-03192009-161901
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)|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1951|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||23 Mar 2009|
|Last Modified:||26 Dec 2012 02:34|
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