Combustion of a Solid Fuel Tube With Contained Liquid Oxidizer in a Hot Gas Atmosphere

Pelosi, Avishag D.; Gany, Alon

doi:10.1080/00102200600809522

Cited by 4 publications

(14 citation statements)

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“…The results indicate that for small droplets the oxidizer will heat up to boiling temperature even before it is revealed on the burning surface, due to heat conduction through the surrounding binder. Stage II is the main stage of the combustion process, as described in other models as well [1][2][3][4][5][6][7][8].U nderstanding the equations that dictate the initiation (stage I) and termination (stage III) processes comes from understanding the second stage.…”

Section: T He Modelmentioning

confidence: 99%

“…The flame height is not uniform due to the diffusion process. Therefore correction factor f c = 0.3 is adopted based on the works of Beckstead [5][6][7],P elosi and Gany [1][2][3][4]:…”

Section: Flame Shapementioning

confidence: 99%

“…Several years ago Pelosi and Gany [1][2][3][4] published their work on solid propellants augmented by liquid encapsulated oxidizer,s howing significantly higher energetic potential than the conventional solid propellants (up to 20 %i n theory). As part of their work [1] Pelosi and Gany investigated the new concept from different aspects, including encapsulating material, strand burning tests, and combustion modeling.…”

Section: Introductionmentioning

confidence: 99%

“…The combustion of as mall size liquid oxidizer droplet within as olid fuel matrix is similar to the combustion of classic solid composite propellant. The well-known BDP model [5][6][7] is a2 Dm odel combining the physical aspects of the process, based on the GDF model [8],a nd the chemical kinetics aspects.This research objective is the development of at ime dependent 2D model, in contrast to the 1D time averaged model that was introduced by Pelosi and Gany several years ago [1][2][3][4].T he current model deals with ap ropellant consisting of ac ontinuous solid matrix containing liquid droplets/capsules of oxidizer,w hich are modeled as cylinders with height equal to diameter,i no rder to simplify the calculations. The current model deals with the sub-critical pressure range, where the oxidizer undergoes three stages in the combustion process:Abstract:Acombustion model of as olid propellant containing liquid oxidizer capsules was developed.…”

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confidence: 99%

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Developing a Combustion Model of a Solid Propellant Containing Capsules of Liquid Oxidizer

Livne

Gany

2015

Propellants Explo Pyrotec

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a] 1I ntroductionComparing solid propellant rocket motors and liquid propellant engines, one can clearly see the great advantage in the simplicity of the solid propellant systems. Yeto nt he other hand, one can also notice the inferior energetic performance of solid motors. The relatively poor energetic performance of the solid propellant rockets stems from the poor energetic properties of available solid oxidizers. Over the past few decades efforts have been made in order to find aw ay to improve the energetic performance of the solid propellants, yet with no significant practical result.Several years ago Pelosi and Gany [1-4] published their work on solid propellants augmented by liquid encapsulated oxidizer,s howing significantly higher energetic potential than the conventional solid propellants (up to 20 %i n theory). As part of their work [1] Pelosi and Gany investigated the new concept from different aspects, including encapsulating material, strand burning tests, and combustion modeling. More complicated models were suggested for solid propellants, but not for this novel propellant, which is based on different physical phenomena (liquid oxidizer submerged in as olid matrix).In the current work, the goal is to develop an ew 2D model for the combustion of as olid matrix containing liquid oxidizer capsules within it. The current model also takes into consideration the changes over time of the nature of the combustion process. 2T he ModelLittle research has been done so far in the subject of combustion of liquid oxidizer droplets contained in asolid polymeric matrix. The combustion of as mall size liquid oxidizer droplet within as olid fuel matrix is similar to the combustion of classic solid composite propellant. The well-known BDP model [5][6][7] is a2 Dm odel combining the physical aspects of the process, based on the GDF model [8],a nd the chemical kinetics aspects.This research objective is the development of at ime dependent 2D model, in contrast to the 1D time averaged model that was introduced by Pelosi and Gany several years ago [1][2][3][4].T he current model deals with ap ropellant consisting of ac ontinuous solid matrix containing liquid droplets/capsules of oxidizer,w hich are modeled as cylinders with height equal to diameter,i no rder to simplify the calculations. The current model deals with the sub-critical pressure range, where the oxidizer undergoes three stages in the combustion process:Abstract:Acombustion model of as olid propellant containing liquid oxidizer capsules was developed. The model is based on the combustion cycle of au nit cell, an oxidizer droplet surrounded by the adjusting amount of binder. Three combustion stages are considered:( 1) binder decomposition parallel to oxidizer heating up to boiling temperature, (2) simultaneous binder and oxidizer gasification, and (3) gasification of the remaining condensed phase species. Simple global kinetics are assumed for the gas phase reactions and binder decomposition abiding Arrhenius law,a nd boiling process for the oxidizer abiding...

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Section: T He Modelmentioning

confidence: 99%

“…The flame height is not uniform due to the diffusion process. Therefore correction factor f c = 0.3 is adopted based on the works of Beckstead [5][6][7],P elosi and Gany [1][2][3][4]:…”

Section: Flame Shapementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Developing a Combustion Model of a Solid Propellant Containing Capsules of Liquid Oxidizer

Livne

Gany

2015

Propellants Explo Pyrotec

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“…Following preliminary experimental investigations [4], the objective of the present work is a first physical modeling and characterization of the combustion behavior of this class of LOESPs to provide a basic prediction capability. For this sake, the model deals with the behavior of a single liquid oxidizer droplet embedded in a solid fuel.…”

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confidence: 99%

Modeling the Combustion of a Solid Fuel Containing a Liquid Oxidizer Droplet

Pelosi

Gany

2012

Journal of Propulsion and Power

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This work presents a physical model of the combustion behavior of a liquid oxidizer droplet with adjacent solid fuel. It is the first modeling attempt related to a proposed new potential class of liquid-oxidizer-enhanced solid propellants, where liquid oxidizer units/capsules are embedded in a solid fuel/propellant, revealing a theoretical specific impulse increase of up to 12%. A one-dimensional mathematical model is formulated, which describes the main characteristics of the microscale flamelet formed by a volatile (typically polymeric) fuel component and an adjacent endothermically evaporating oxidizer droplet. The model predicts fuel and oxidizer surface temperatures, fluxes, and flame height as functions of operating pressure and droplet size. The transient nature of the combustion process is emphasized, revealing a combustion cycle at the individual droplet scale, with pressure-dependent average burning rates typical to solid propellants.

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Statistical model for combustion of high-metal magnesium-based hydro-reactive fuel

Chao

Xia

et al. 2012

Chinese Phys. B

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We investigate experimentally and analytically the combustion behavior of a high-metal magnesium-based hydro-reactive fuel under high temperature gaseous atmosphere. The fuel studied in this paper contains 73% magnesium powders. An experimental system is designed and experiments are carried out in both argon and water vapor atmospheres. It is found that the burning surface temperature of the fuel is higher in water vapor than that in argon and both of them are higher than the melting point of magnesium, which indicates the molten state of magnesium particles in the burning surface of the fuel. Based on physical considerations and experimental results, a mathematical one-dimensional model is formulated to describe the combustion behavior of the high-metal magnesium-based hydro-reactive fuel. The model enables the evaluation of the burning surface temperature, the burning rate and the flame standoff distance each as a function of chamber pressure and water vapor concentration. The results predicted by the model show that the burning rate and the surface temperature increase when the chamber pressure and the water vapor concentration increase, which are in agreement with the observed experimental trends.

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Combustion of a Solid Fuel Tube With Contained Liquid Oxidizer in a Hot Gas Atmosphere

Cited by 4 publications

References 2 publications

Developing a Combustion Model of a Solid Propellant Containing Capsules of Liquid Oxidizer

Developing a Combustion Model of a Solid Propellant Containing Capsules of Liquid Oxidizer

Modeling the Combustion of a Solid Fuel Containing a Liquid Oxidizer Droplet

Statistical model for combustion of high-metal magnesium-based hydro-reactive fuel

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