Design and performance of a vaporized type fuel inlet system
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Authors
Miller, Winston L.
Subjects
Advisors
Murphy, Thomas E.
Hall, Newman A.
McManus, Howard N.
Date of Issue
1954
Date
Publisher
University of Minnesota
Language
en_US
Abstract
A vaporizing tube fuel inlet system was developed experimentally for a constant pressure 2 x 5 x 20 inch rectangular combustion chamber. Naphtha was used as the fuel at a design flow rate of .3#/min. The chamber was operated at a primary air/fuel ratio of 36/1, an over-all air/fuel ratio of 125/1, and a full section velocity of 125 ft/sec. The resulting vaporizer required a substantially shorter primary combustion zone than a comparable spray injection system. The curves of efficiency versus fuel/air ratio were relatively flat showing little drop in efficiency as fuel flow rate was increased or decreased from peak conditions. The flame was blue having little luminosity. However, there was evidence that the good results were in part due to the high volatility of the fuel, and that insufficient heat was being transferred by the vaporizer. The three quench air patterns tested were not effective in quenching combustiont and the resulting exhaust temperature profiles had high temperature peaks and were unsatisfactory for use with a turbine.
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Sponsors
This project was sponsored by the U.S. Navy through its facility for advance technical training, the U.S. Naval Postgraduate School