Propulsion System Flow Stability Program (Dynamic). Part XII. Unsteady Combustion in Duct Burners and Afterburners

Item

Title
Propulsion System Flow Stability Program (Dynamic). Part XII. Unsteady Combustion in Duct Burners and Afterburners
Date
1968
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
AFAPL TR 68-142 Part XII
Creator
Dix, D. M.
Duffield, P. L.
Smith, J. E.
Corporate Author
North American Rockwell Corp Los Angeles CA Los Angeles Div
Laboratory
Air Force Aero Propulsion Laboratory
Extent
246
NTRL Accession Number
AD852024
Identifier
AD0852024
Access Rights
Export Control
Distribution Classification
1
Contract
F33615-67-C-1848
DoD Project
None Given
DoD Task
None Given
DTIC Record Exists
No
Distribution Change Authority Correspondence
PER AFAPL LTR
Date Modified
Scanned by request 8/3/2006 submitted by a Private Citizen (No Known Affiliation)
Abstract
An analytical model of combustion instability in afterburners and duct burners has been formulated which incorporates in a readily identifiable way the significant loss and gain processes associated with oscillatory combustion. The dominant loss mechanisms, as revealed by a literature survey and subsequent assessment, are those due to convection and radiation from the nozzle and absorption by acoustic liners. The gain mechanisms have been incorporated in a general way which permits physical interpretation; those mechanisms considered to be of most importance in aircraft burners are those associated with fuel vaporization and turbulent transport processes. The analytical model is also capable of treating approximately the significant nonlinear aspects of combustion instability associated with the dependencies of the major losses and gains on oscillation amplitude. The total mathematical requirements to obtain numerical results are the solution of transcendental algebraic equations and the evaluation of definite integrals. An application of the model to a known experimental situation yielded results which were qualitatively correct and quantatively of the correct order of magnitude. Finally, a test plan has been formulated to enable the adequacy of the analytical model to be further assessed.
Report Availability
Full text available
Date Issued
1968-12
Publisher
Wright-Patterson Air Force Base, OH : Air Force Aero Propulsion Laboratory, Air Force Systems Command
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFAPLTR68-142part12.pdf