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Combustion stability analysis of preburners in liquid propellant rocket engines during shutdownA linearized one-dimensional lumped-parameter model capable of predicting the occurrence of the low frequency combustion instability (chugging) experienced during preburner shutdown in the Space Shuttle Main Engines is discussed, and predictions are compared with NASA experimental results. Results from a parametric study of parameters including chamber pressure, fuel and oxygen temperatures, and the effective bulk modulus of the liquid oxidizer suggest that chugging is probably affected by conditions at shutdown through the fuel and oxidizer temperatures. It is suggested that chugging is initiated when the fuel, oxidizer, and helium temperature and flow rates pass into an unstable region, and that chugging may be terminated by decaying pressures.
Document ID
19870057923
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lim, Kair-Chuan
(Tennessee Univ. Knoxville, TN, United States)
George, Paul E., II
(Tennessee, University Knoxville, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1987
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 87-1776
Accession Number
87A45197
Distribution Limits
Public
Copyright
Other

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