Transient Thermochemical Erosion Modeling for Solid Propellant Rocket Motor Nozzles Including the Effect of Shape Change and Anisotropy

Date

2018-06-25

Author

Onay, Oğuz
Eyi, Sinan

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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In this study, a loosely coupled thermochemical erosion model is developed for the nozzle throat erosion calculations of the solid propellant rocket motors. The flow is assumed to be quasi-steady and the solid domain is updated at each time step of the solid conduction solution. Flow and solid domains are assumed to be axisymmetric. Heterogeneous finite rate surface reactions are used on the wall surface and mass and energy balances are implemented. Effects of anisotropy and the shape change are included to the model. A Landau-like grid advection term is used for the heal conduction solution while contracting the grid of the axisymmetric solid domain. Navier-Stokes equations in conservative variable form are solved to evaluate the flow field inside the nozzle and water-gas shift reaction is included to the flow solution. Calculated erosion rates are compared with results from the literature. Besides, the lime accuracy of the model is tested with the post-firing measurements of a test motor. Short firing duration tests are preferred for the comparison, rather than firings that the diffusion limited erosion regime is reached.

URI

https://hdl.handle.net/11511/35587

DOI

https://doi.org/10.2514/6.2018-3719

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Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

O. Onay and S. Eyi, “Transient Thermochemical Erosion Modeling for Solid Propellant Rocket Motor Nozzles Including the Effect of Shape Change and Anisotropy,” 2018, vol. 2018, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/35587.