NDLI: Axial-slot air admission for controlling performance of a one-quarter-annulus turbojet combustor and comparison with complete engine

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Axial-slot air admission for controlling performance of a one-quarter-annulus turbojet combustor and comparison with complete engine

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1952
Description	An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted to demonstrate the application of certain design principles to the control of outlet-gas temperature distributions. Comparisons of performance of a one-quarter-annulus combustor (duct-type installation) and a full-annulus combustor (obtained in a full-scale turbojet engine) are presented to indicate the applicability of results obtained from combustion studies conducted in duct-type installations. A reasonable correlation existed between the performance of the one-quarter-annulus and full-annulus combustors except for temperature distribution. Sufficient trends did exist which made it possible to predict temperature distributions for the engine, although absolute correlation did not exist. A radial temperature distribution similar to that required for a given engine was obtained using a one-quarter-annulus duct-type setup to predict results.
File Size	17912443
Page Count	45
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930087859
Archival Resource Key	ark:/13960/t4rj8sn85
Language	English
Publisher Date	1952-03-24
Access Restriction	Open
Subject Keyword	Combustion--turbine Engines Engines, Turbo-jet Combustion Research--general Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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