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Liquid rocket combustion instability analysis by CFD methodsCombustion instability in liquid rocket engines is simulated computationally by using a simple two-parameter model for the combustion response function. The objectives of the study are to assess the capabilities of CFD algorithms for instability studies and to investigate the response to parametric effects such as bombs and distributed combustion. Results indicate that numerical solutions of high accuracy can be obtained if a sufficient number of grid points are used per wavelength of the disturbance. The short-term response to bombs or pulses triggers a large number of modes in the combustor whose faithful resolution requires highly dense grids, although there is evidence that correct long-term solutions can be obtained even if all the short-term frequencies are not resolved. Long-term responses to pulses are shown to decay to the most unstable mode in small amplitude cases, and to exhibit limit cycles in large amplitude cases. Comparison of distributed with concentrated heat release indicates the former is more stable for given values of the combustion response parameters, and that the distributed heat release gives rise to higher frequency disturbances. Wave steepening is observed in the solutions, but its effect is less pronounced in multidimensional waves than in one-dimensional waves.
Document ID
19910059498
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Grenda, J. M.
(Pennsylvania State Univ. University Park, PA, United States)
Venkateswaran, S.
(Pennsylvania State Univ. University Park, PA, United States)
Merkle, C. L.
(Pennsylvania State University University Park, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 91-2085
Accession Number
91A44121
Funding Number(s)
CONTRACT_GRANT: NAGW-1356
Distribution Limits
Public
Copyright
Other

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