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Multi-dimensional analysis of combustion instabilities in liquid rocket motorsA three-dimensional analysis of combustion instabilities in liquid rocket engines is presented based on a mixed finite difference/spectral solution methodology for the gas phase and a discrete droplet tracking formulation for the liquid phase. Vaporization is treated by a simplified model based on an infinite thermal conductivitiy assumption for spherical liquid droplets of fuel in a convective environment undergoing transient heating. A simple two parameter phenomenological combustion response model is employed for validation of the results in the small amplitude regime. The computational procedure is demonstrated to capture the phenomena of wave propagation within the combustion chamber accurately. Results demonstrate excellent amplitude and phase agreement with analytical solutions for properly selected grid resolutions under both stable and unstable operating conditions. Computations utilizing the simplified droplet model demonstrate stable response to arbitrary pulsing. This is possibly due to the assumption of uniform droplet temperature which removes the thermal inertia time-lag response of the vaporization process. The mixed-character scheme is sufficiently efficient to allow solutions on workstations at a modest increase in computational time over that required for two-dimensional solutions.
Document ID
19920071530
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Grenda, Jeffrey M.
(NASA Headquarters Washington, DC United States)
Venkateswaran, Sankaran
(NASA Headquarters Washington, DC United States)
Merkle, Charles L.
(Pennsylvania State University University Park, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 92-3764
Accession Number
92A54154
Funding Number(s)
CONTRACT_GRANT: NAGW-1356
Distribution Limits
Public
Copyright
Other

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