Gas-Particle Mixture Flows in a Spinning Solid Rocket Motor

概要

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Main aim of this studiy is to clarify the spin stabilization effect on the flow field. Internal flow field of the solid rocket motor is numerically analyzed by the time-dependent finite difference method in combination with the boundary-fitted curvilinear coordinate technique. Computation was carried out about flow through the nozzle with cigarette-burn type chamber and also with spherical chamber. The thrust performance and the behavior of the particle impingement upon nozzle wall were analyzed. As the results, the followings are shown, (1) The thrust loss caused by two-phase flow is less for the nozzle with cigarette-burn type chamber, than for the nozzle with spherical chamber. (2) As to the nozzle with cigarette-burn type chamber, the thrust loss of 2 to 3 percent occurs under the 2 r.p.s. spin stabilization. In no-spin case, particle impingement is not observed over a whole nozzle wall, while in the case of spin stabilization it is observed on the nozzle wall near the exit. (3) As to the nozzle with spherical chamber, there is no appreciable effect of the spin stabilization.
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