The analytical design of a turbo-jet combustion chamber.

A "can" type combustion chamber was designed using all available proved concepts. A survey of existing designs was made to arrive at a logical design point. The fact that parallel flow would exist within the chamber was noted, and the burner was designed to obtain the required flow within an equal pressure drop across all the parallel paths. The holes for introducing the hair into the burner basket were placed in such a manner that the total area into the burner basket, plotted against distance downstream, fell on an arc of a circle. This made the design follow several proved concepts automatically. The performance was calculated and compared with existing designs. The comparison was quite favorable, with the exception of combustion efficiency. Since the empirical equation for combustion efficiency was obtained from tests under slightly different conditions than the design point, doubt exists as to the validity of the values obtained by its use.

Department dc:contributor.department

Aeronautical Engineering

Grantor dc:publisher

University of Minnesota

Year dc:date.issued

1949

Author dc:creator

• Verdin, James Bernard

Handle dc:identifier.uri

https://hdl.handle.net/10945/35710

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/35710