Burn rate (chemistry)

About: Burn rate (chemistry) is a research topic. Over the lifetime, 847 publications have been published within this topic receiving 8908 citations. The topic is also known as: Burning rate.

Rocket propellant charge with negative pressure exponent

Abstract: A solid propellant charge for a rocket motor or gas generator, the charge having a selected bulk propellant (2) with longitudinal cores of control material (3). The control cores have a burning rate, greater than that of the bulk propellant, which decreases as pressure increases, so that the solid propellant charge has a burning rate which also decreases as pressure increases.

Flame Propagation of Bio-Ethanol in a Constant Volume Combustion Chamber

Abstract: This research presents an experimental study of the combustion of ethanol blends with gasoline in a constant volume combustion chamber. The test fuels are gasoline, E20 (ethanol20%), E85 (ethanol85%) and pure ethanol. The pressure in combustion chamber was measured. The images of flame propagation were recorded by schlieren technique with high speed video camera. The effects of equivalent ratio, temperature, pressure on the combustion characteristics were studied. The results show the greater percent of ethanol provides faster burn rate of combustion and higher peak of cylinder pressure. The peak combustion pressure E100 is 0.873 MPa which is higher than E85, E20 and E0. The ignition delay time decreases with higher percent of ethanol. As the results of flame propagation images, at stoichometric burn duration of pure ethanol is 13 ms which is shorter than E85, E20 and E0. The combustion duration of mixture at equivalence ratio of 1.0 is less than that of equivalent ratio 0.8, 1.2 and 1.4. The flame speed and peak pressure increase with percentage of ethanol. The faster flame speed of ethanol flame effects to shorter combustion duration and greater performance and efficiency.

Electrothermal-Chemical (ETC) Temperature Sensitivity of JA2 7 Perf Propellant

Abstract: : The temperature sensitivity of JA2 7 perf propellant was studied by conditioning it to 21.1 deg C, 48.9 deg C, and -31.7 deg C. The firings were conducted in a 120-cc closed chamber, conventionally and with plasma injection (ETC), using a 1.2-ms pulse width provided by four banks of a 400 kJ PFN (Pulse Forming Network). The study showed a decrease in the burn rate between the ETC firings at 21.1 deg C and the conventional at the same temperature, but it showed an increase in the burn rate for the 48.9 deg C and -31.7 deg C cases, respectively.

Predicting effects of oxidizer content and particle size on NEPE combustion characteristics

Abstract: On the basis of an analysis and investigation on thermal behavior and combustion model of the high energy solid propellant,considering the combustion characteristics of NEPE propellant,the burning rate and pressure exponent equation of NEPE was derived based on the chemical structure.In the light of this model,a computer program is compiled to compute the burning rate and its pressure exponent.The effects of oxidizer(AP,RDX and HMX) content and particle size on the propellants combustion characteristics are studied systematically.The results show that most of calculated results are within the ten percent relative error range of the experimental values.It proves that the model and the program are reasonable.