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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.


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Patent
27 Dec 1991
TL;DR: A stable chlorine-free solid rocket propellant composition containing a low energy binder component having an HEX value not exceeding about 0 cal/gm and comprising, in combination, a Nitrate salt and/or phase stabilized nitrate salt as oxidizer component, a Mg/Al alloy of limited Mg content as a fuel component, at least one energetic plasticizer component and a burn rate catalyst is presented in this article.
Abstract: A stable chlorine-free solid rocket propellant composition containing a low energy binder component having an HEX value not exceeding about 0 cal/gm and comprising, in combination, a nitrate salt and/or phase stabilized nitrate salt as oxidizer component, a Mg/Al alloy of limited Mg content as a fuel component, at least one energetic plasticizer component, and a burn rate catalyst.

11 citations

Proceedings ArticleDOI
05 May 2009
TL;DR: In this article, a method for inducing vortical flow that combines vortex and axial oxidizer injection within a cylindrical, interior burning fuel grain was proposed to increase the performance of a hybrid rocket motor.
Abstract: : A hybrid rocket motor is a type of rocket motor where fuel is placed in a combustion chamber as a solid, and then gaseous or liquid oxidizer is injected. When the two mix and are ignited, the surface of the fuel burns and the gases produced in the combustion develop thrust. Hybrid rocket motor performance is dictated by the rate at which the fuel burns. Fuel burn rate (or regression rate) can be increased by increasing oxidizer flow speed over the burning fuel surface. This is because flow over the burning surface creates shear stress which facilitates fuel and oxidizer mixing. One method for improving shear stress and thus regression rate is to induce an oxidizer vortex in the combustion chamber. The subject of this research is a method for inducing vortical flow that combines vortex and axial oxidizer injection within a cylindrical, interior burning fuel grain. A hybrid motor test stand has been developed to test both axial and vortex oxidizer flow configurations as well as any combination of the two. The apparatus is capable of measuring thrust, oxidizer flow rate, and chamber pressure. This, along with physical measurements of fuel grains, allows the determination of fuel regression rate, combustion efficiency, and specific impulse, all key rocket performance parameters. The apparatus is also equipped with millisecond scale combustion analyzers to measure the gases in the combustion products, to include CO, CO2, NOx, and unburned hydrocarbons. The high sample rate of these analyzers sheds light on vortex hybrid combustion processes as well as the phenomenon which could lead to combustion instability. Overall, this research is focused on identifying a possible way to increase hybrid rocket performance in order to bring this very safe and efficient type of propulsion to maturity.

11 citations

Journal ArticleDOI
TL;DR: In this article, a 16% aluminum polybutadiene acrylic acid (PBAA) propellant was added to a 2-in. web motor at pressure levels from 300 to 1200 psia with centrifugal accelerations from 0 to 140 g.
Abstract: Experimental results concerning the transient burning-rate augmentation of a 16% aluminum polybutadiene acrylic acid (PBAA) propellant burned in a 2-in. web motor at pressure levels from 300 to 1200 psia with centrifugal accelerations from 0 to 140 g. The orientation of the acceleration vector was varied to determine its effect on the transient burning rate. The burning-rate augmentation was strongly dependent on (1) acceleration level, (2) propellant distance burned (or burn time), and (3) orientation of the acceleration vector with respect to the burning surface. This transient rate augmentation resulted from the retention of molten metallic residue on the burning surface by the normal acceleration loading. The presence of the residue altered the combustion zone heat transfer and caused increased localized burning rates, as evidenced by the pitted propellant surfaces that were observed from extinction tests conducted at various acceleration levels.

11 citations

Journal ArticleDOI
TL;DR: In this paper, the burning rate behavior of a series of bimodal PETN/Polyurethane (PU) and RDX/PU propellants have been examined to determine the effect of binder and oxidizer concentration, and coarse to fine ratio of oxidizer particles on burn rate.
Abstract: The burning rate behaviour of a series of bimodal PETN/Polyurethane (PU) and RDX/PU propellants have been examined to determine the effect of binder and oxidizer concentration, and coarse to fine ratio of oxidizer particles on burn rate. Evidence for an oxidizer interaction has been found in mixed PETN/RDX/PU propellants. Catalysis of the PETN/PU, RDX/PU and PETN/RDX/ PU propellants by a metal oxide has been investigated. Catalytic enhancement in both the condensed phase and gas phase has been observed. Oxidizer interaction between PETN and RDX can lead to substantial increases in burning rate in the presence of catalyst.

10 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202310
202220
202116
202015
201918
201811