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LINEAR THROTTLING HIGH REGRESSION RATE VORTEX FLOW FIELD INJECTION SYSTEM WITHIN A HYBRID ROCKET ENGINE
LINEAR THROTTLING HIGH REGRESSION RATE VORTEX FLOW FIELD INJECTION SYSTEM WITHIN A HYBRID ROCKET ENGINE
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机译:混合火箭发动机内的线性节流高回归速率涡流场注射系统。
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摘要
A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference to comprise an outer edge of a solid propellant grain in the hybrid rocket engine. The engine also includes an injection system that has a throttle valve and an injector that injects injection fluid into the engine and produces a vortex flow-field for the injected fluid. The injector includes at least one primary feed line that distributes the injection fluid throughout a pre-swirl chamber and multiple orifices along an inner edge of the injection chamber. The pre-swirl chamber connects to the injection chamber and at least one of the primary feed lines and redirects a primary fluid flow of the injected fluid from a primary axial direction to a centrifugal direction.
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