Importance

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Abstract

There is disclosed in combination with a solid fuel-propellant grain 24 having an axially extending aperture 26, particularly of a hybrid rocket motor, an oxidizer inlet 20 at one end and a combustion gas outlet 22 at the other end, a tubular oxidizer injector 32 disposed in the inlet and extending axially in the grain aperture. The tubular injector comprises a tube 34 containing a plurality of oxidizer injection orifices 38 in the outer circumference of the tube to discharge fluid streams of oxidizer into the fuel grain aperture for combustion of the fuel grain. Additional oxidizer orifices, e.g. in the form of shower head orifices 44, are disposed in the downstream end of the tube. A body member or plug 46 is axially positioned in the tube 34, the plug having an outside diameter smaller than the inside diameter of the tube, and a length less than the length of the tube, and providing an annular channel 50 for the flow of oxidizer, to thereby increase the flow of oxidizer in the injector tube and provide cooling by the oxidizer flowing therein. The tubular injector provides uniform injection of liquid oxidizer, and uniform rapid vaporization of oxygen and combustion stability.

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First Claim