2013
DOI: 10.2514/1.b34791
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Chemical Erosion of Carbon-Phenolic Rocket Nozzles with Finite-Rate Surface Chemistry

Abstract: Ablative materials are commonly used to protect the nozzle metallic housing and to provide the internal contour to expand the exhaust gases in solid rocket motors. Because of the extremely harsh environment in which these materials operate, they are eroded during motor firing with a resulting nominal performance reduction. The objective of the present work is to study the thermochemical erosion behavior of carbon-phenolic material in solid rocket motor nozzles. The adopted approach relies on a validated full N… Show more

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Cited by 64 publications
(24 citation statements)
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“…In the present study the modeling of gas-surface interaction already developed and validated for ablating surfaces [15][16][17][18][19] is extended to the case of fuel pyrolysis in hybrid rocket engines. In particular, a detailed finiterate gas/surface interaction model is coupled with a three-dimensional chemically-reacting fluid dynamics (CFD) code.…”
Section: Theoretical and Numerical Modelmentioning
confidence: 99%
“…In the present study the modeling of gas-surface interaction already developed and validated for ablating surfaces [15][16][17][18][19] is extended to the case of fuel pyrolysis in hybrid rocket engines. In particular, a detailed finiterate gas/surface interaction model is coupled with a three-dimensional chemically-reacting fluid dynamics (CFD) code.…”
Section: Theoretical and Numerical Modelmentioning
confidence: 99%
“…Evaluation of the nozzle inner wall temperature To evaluate the inner wall temperature of the nozzle the thermal resistance approach was used. This strategy is justified because despite the outer wall has a very long transient the inner wall rapidly reach the steady state condition [5]. Since the inner surface of the tube suffers a continuous regression, the energy balance in the internal boundary can be expressed as:…”
Section: 2mentioning
confidence: 99%
“…In this context, it is of great interest to predict the efficacy of insulation protection system on a SRM and its behavior during operating time. Several ablation models and computational tools have been developed in order to study the ablation mechanism, with several levels of complexity [3,4,5].…”
Section: Introductionmentioning
confidence: 99%
“…In the present study, the modeling of the gas/surface interaction already developed and validated for ablating surfaces [25][26][27][28][29] is extended to the case of fuel pyrolysis in hybrid rocket engines. In particular, a detailed finite-rate gas/surface interaction model is coupled with a three-dimensional chemically reacting fluid dynamics code.…”
Section: Theoretical and Numerical Modelmentioning
confidence: 99%