Topic
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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TL;DR: In this paper, the effect of the initial temperature on the burning rate of the JANNAF standard composite propellant was investigated using four combustion models: the granular diffusion flame model based on the uniformly distributed heat release (KTSS) model, the Beckstead, Derr, and Price (BDP) multiple flame model, a modified BDP model, and the petite ensemble model.
11 citations
TL;DR: In this paper, a single-zone model based on conservation equations for mass, energy and oxygen concentration is proposed to assess the burning rate of a pool fire in a well-confined and mechanically-ventilated room using a single zone model.
Abstract: The objective of this work is to provide a ‘support tool’ to assess the burning rate of a pool fire in a well-confined and mechanically-ventilated room using a single-zone model based on conservation equations for mass, energy and oxygen concentration. Such configurations are particularly relevant for nuclear facilities where compartments are generally sealed from one another and connected through a ventilation network. The burning rates are substantially affected by the dynamic interaction between the fuel mass loss rate and the rate of air supplied by mechanical ventilation. The fuel mass loss rate is controlled by (i) the amount of oxygen available in the room (i.e. vitiation oxygen effect) and (ii) the thermal enhancement via radiative feedback from the hot gas to the fuel surface. The steady-state burning rate is determined by the ‘interplay’ and balance between the limiting effect of oxygen vitiation and the enhancing effect of radiative feedback. An extensive sensitivity study over a wide range of fuel areas and mechanical ventilation rates shows that a maximum burning rate may be obtained. For the studied HTP (Hydrogenated Tetra-Propylene) pool fires, the maximum burning rate is up to 1.75 times the burning rate in open air conditions.
11 citations
11 Jul 2004
TL;DR: In this article, a mixed-hybrid propulsion concept that is both controllable and safe was evaluated at the University of Alabama in Huntsville Propulsion Test Facility to determine fundamental ballistic properties.
Abstract: The objective of this project is to experimentally characterize the ballistic properties of a mixed-hybrid propulsion concept that is both controllable and safe. The propulsion configuration was a center-perforated grain with gaseous oxidizer injected at the head end. The fuel grains were loaded with low levels of oxidizer and additives that enhanced their density, and increased the solid regression rate. The propellant formulations have been formulated using a design of experiments approach that evaluates the effects of three ingredients. They were evaluated at the University of Alabama in Huntsville Propulsion Test Facility to determine fundamental ballistic properties that are necessary inputs to designers for system evaluations. The results show that the ingredients added to the solid grain produces up to a 150-300% augmentation in the solid burning rate when compared to grains without any additives at the same flux and pressure levels. The burning rate was determined to be both a function of pressure and oxidizer flux. The propellant with the 25% ammonium perchlorate and the additive burned the fastest. The propellants will stop burning when the gaseous oxidizer flow is stopped.
11 citations
01 Jan 1963
TL;DR: Aluminum additive in unstable combustion of solid rocket propellants - growth, evaporation and burning rates in flame zone as discussed by the authors, which is used for propulsion of a single-stage rocket.
Abstract: Aluminum additive in unstable combustion of solid rocket propellants - growth, evaporation and burning rates in flame zone
11 citations
TL;DR: In this paper, the sensitivity of burning rate to propellant temperature has been expressed in the form of two different temperature coefficients, one describing the effect of temperature on the burning rate in a constant pressure environment, and the other describing the impact of temperature in a solid rocket motor.
11 citations