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- W2367525323 abstract "A numerical study on a solid rocket motor nozzle is conducted to analyze the flow,heat transfer and thermo-structure performance. Reynolds Stress viscous model and enhanced wall function are used to solve Navier-Stokes equations. By setting the inner wall temperature distribution as boundary condition,the two-dimensional axisymmetric transient heat transfer equation is solved. By loading the temperature field by step time,a transient static structure analysis is proposed. The flow field,temperature field and stress field are obtained. The results show that for this nozzle,spinning lead to a severe change in inner wall temperature distribution especially at nozzle insert and the divergent section when speed is 100 r /min and 600 r /min. A coupled effect of spinning flow field and structure results in severe heat transfer especially erosion of nozzle insert. The temperature of the characteristic points increases along with the spinning speed. The maximum Von-Mises stress is at end of the outermost. The entire stress can released when spinning speed is lower than 100 r /min. The maximum Von-Mises stress of the nozzle and the characteristic point at divergent section increases with the spinning speed,while the characteristic point at nozzle insert decreases because of temperature gradient decreasing leading by spinning." @default.
- W2367525323 created "2016-06-24" @default.
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- W2367525323 date "2014-01-01" @default.
- W2367525323 modified "2023-09-23" @default.
- W2367525323 title "Thermo-Structural Analysis of Spinning SRM Nozzle" @default.
- W2367525323 hasPublicationYear "2014" @default.
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