Comparison of Temperature Computation Methods for Nozzle in SRM

Xiao Ya Zheng; Peng Li

doi:10.4028/www.scientific.net/AMM.152-154.1253

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 152-154Comparison of Temperature Computation Methods for...

Comparison of Temperature Computation Methods for Nozzle in SRM

Abstract:

The precondition of structure integrality analysis for nozzle is temperature computation. Considering the close coupling of flow and heat transfer, thermal conditions should be treated with coupled heat transfer. The paper aimed at a typical nozzle and compared with temperatures using the universal method and the coupled method. The results show that temperature distribution laws on internal wall of two methods are similar, but not exactly the same. The radiation is the major heating form in nozzle inlet and should be considered in temperature computation. The coupled method is more reasonable and convenient to consider radiation and ablation. The coupling of flow, heat transfer，ablation and structure deformation is the development trend for future structure integrality analysis for nozzle in SRM.

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Periodical:

Applied Mechanics and Materials (Volumes 152-154)

Pages:

1253-1257

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.152-154.1253

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Online since:

January 2012

Authors:

Xiao Ya Zheng, Peng Li

Keywords:

Coupled Heat Transfer, Fluid-Structure Coupled Method, Nozzle, Solid Rocket Motor (SRM), Temperature Field

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References

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