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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Efficiency evaluation of two-stage turbine with low ratio of blade to jet speed suitable for bleed-type high energy liquid rocket applications
This is the sixth yearly report on the research at Princeton University on the problem of combustion instability in liquid-propellant rocket motors. These investigations have been sponsored by the National Aeronautics and Space Administration under NASA Contract NASr-217 and, in the past, under NASA Grant NsG-99-60. The nonlinear aspects of the problem have been emphasized in both the theoretical and experimental portions of the program. Presently, the theoretical research primarily involves studies of possible mechanisms or forcing functions of the instabilities, the nonlinear gasdynamic oscillations associated with instability in rocket motors, the effect of the exhaust nozzle on the stability, and the effect of damping devices on the stability. In conjunction with the theoretical program, an experimental program of an equally broad range is being conducted. This program includes basic experiments both with rocket motors and "cold" chambers which have been designed to study various combustion processes in order to provide understanding which would be useful in the construction of a theoretical model. It also includes studies of the effects of exhaust nozzles and damping devices upon the instability as well as controlled testing of liquid rocket motors with parametric variations intended to determine the factors which strongly influence the incidence of nonlinear combustion instability.
Wall temperature and heat transfer patterns in liquid-propellant rocket thrust chamber coolant channels
Combustion instability in liquid propellant rocket motors causing pressure fluctuations
Heterogeneous detonations, discussing polydisperse and monodisperse spray detonations and liquid fuel film shock-induced combustion
Metals for liquid propellant rocket systems in terms of environments in which performance is required
Heterogeneous detonations, discussing polydisperse and monodisperse spray detonations and liquid fuel film shock-induced combustion
Heat sterilization of pyrotechnics and spacecraft onboard liquid and solid propulsion subsystems
Heat sterilizability of liquid hydrazine propulsion system
Longitudinal vibration characteristics of scaled dynamic model of liquid propellant multistage launch vehicle
Transient pressure measuring methods as applied to liquid propellant rocket thrust chamber
Silicon semiconductor combustion pressure transducer for high temperature HF pressure measurements within liquid rocket motor chambers
Fuel consumption precision measurements for low thrust auxiliary rockets using impeller wheel and photometric devices
Liquid rocket propellants use in U.S. space program, particularly Apollo project, discussing future trends
Frequency pattern analysis for liquid rocket pump fluid cavitation characteristics
S-IVB liquid rocket engine and propellant feed systems restart chilldown in orbital operations
S-IVB liquid rocket engine and propellant feed systems restart chilldown in orbital operations
Consideration of the problem of reducing the probability of mechanical failure of bladder systems used for the expulsion of propellants into liquid rocket engines. It is shown that individual local folds in collapsing bladders can be classified into single and double folds, specifiable by nondimensional geometrical parameters which directly define the maximum strains at these folds. From these maximum strains the number of collapse/inflation cycles to failure can be obtained from low-cycle fatigue data experimentally determined for the bladder material of interest. Cycle life data are presented in terms of true maximum strain for four metals, two plastics, and two elastomers. It is found that double folds give rise to much more severe folding strains than do simple folds.