Thermal protection of rocket nozzle by using film cooling technology - effect of lateral curvature
| Autor: | Abdelmadjid Boudjemai, A. Guelailia, Jin Wang, Azzeddine Khorsi |
|---|---|
| Rok vydání: | 2018 |
| Předmět: |
Fluid Flow and Transfer Processes
Materials science business.product_category business.industry Turbulence Mechanical Engineering Rocket engine nozzle 02 engineering and technology Mechanics Propulsion Computational fluid dynamics Condensed Matter Physics Curvature 01 natural sciences 010305 fluids & plasmas 020303 mechanical engineering & transports 0203 mechanical engineering Rocket Mass transfer 0103 physical sciences Shear stress business |
| Zdroj: | International Journal of Heat and Technology. 36:1070-1074 |
| ISSN: | 0392-8764 |
| DOI: | 10.18280/ijht.360338 |
| Popis: | The present paper aims to analyze the applicability of film cooling method to a rocket as a thermal protection. Lateral curvature effect on film cooling performance through a single row of cylindrical holes with different spanwise angles is investigated. Four different lateral curvature cases (C = ∞, 100, 60, 20) with four inclination angles of cooling injection holes (β= 35°, 45°, 55°, 65°) are considered. The ANSYS CFX has been used for this computational simulation. The turbulence is approximated by a shear stress transport model (SST). Detailed film effectiveness distributions are presented for several blowing ratios (0.5, 1 and 1.5). The numerical results are compared with experimental data. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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