NDLI: Effect of axially staged fuel introduction on performance of one-quarter sector of annular turbojet combustor

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Effect of axially staged fuel introduction on performance of one-quarter sector of annular turbojet combustor

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1953
Description	The design principle of injecting liquid fuel at more than one axial station in an annual turbojet combustor was investigated. Fuel was injected into the combustor as much as 5 inches downstream of the primary fuel injectors. Many fuel-injection configurations were examined and the performance results are presented for 11 configurations that best demonstrate the trends in performance obtained. The performance investigations were made at a constant combustor-inlet pressure of 15 inches of mercury absolute and at air flows up to 70 percent higher than values typical of current design practice. At these higher air flows, staging the fuel introduction improved the combustion efficiency considerably over that obtained in the combustor when no fuel staging was employed. At air flows currently encountered in turbojet engines, fuel staging was of minor value. Radial temperature distribution seemed relatively unaffected by the location of fuel-injection stations.
File Size	11440358
Page Count	29
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930087572
Archival Resource Key	ark:/13960/t3jx2qk3d
Language	English
Publisher Date	1953-03-30
Access Restriction	Open
Subject Keyword	Combustion - Effect OF Engine Operating Conditions AND Combustion-chamber Geomet Combustion - Turbine Engines Combustion - Effects OF Fuel Atomization 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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