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Prediction of swirling reacting flow in ramjet combustorsNumerical computations have been undertaken for a basic two-dimensional axisymmetric flowfield which is similar to that found in conventional gas turbine and ramjet combustors. A swirling flow enters a larger chamber via a sudden or gradual expansion. The calculation method involves a staggered grid system for axial and radial velocities, a line relaxation procedure for efficient solution of the equations, a two-equation turbulence energy-turbulence dissipation rate turbulence model, a stairstep boundary representation of the expansion flow, and realistic accommodation of swirl effects. The results include recirculation zone characterization and predicted mean streamline patterns. Predictions with and without chemical reaction are obtained. An associated isothermal experimental flow study is providing a useful data base. Successful outcomes of the work can be incorporated into the more combustion- and hardware-oriented activities of industrial concerns.
Document ID
19810056499
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lilley, D. G.
(Oklahoma State University Stillwater, OK, United States)
Samples, J. W.
(U.S. Military Academy West Point, NY, United States)
Rhode, D. L.
(Oklahoma State Univ. Stillwater, OK, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 81-1485
Meeting Information
Meeting: Joint Propulsion Conference
Location: Colorado Springs, CO
Country: US
Start Date: July 27, 1981
End Date: July 29, 1981
Sponsors: SAE, AIAA, ASME
Accession Number
81A40903
Funding Number(s)
CONTRACT_GRANT: NAG3-74
Distribution Limits
Public
Copyright
Other

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