초록 ▼

A rocket nozzle having an inlet, a middle region, a throat and an outlet, wherein a ratio of the cross-sectional area of the inlet to the throat is about 1.1. The middle region preferably has a shape which rises to an apex. Such a configuration places particles resulting from combustion on a traject

A rocket nozzle having an inlet, a middle region, a throat and an outlet, wherein a ratio of the cross-sectional area of the inlet to the throat is about 1.1. The middle region preferably has a shape which rises to an apex. Such a configuration places particles resulting from combustion on a trajectory which misses the wall of the nozzle at the throat or choke point, thereby decreasing throat erosion/ablation.

대표청구항 ▼

[ What is claimed is:] [1.]1. A rocket nozzle comprising:a nozzle member having an inlet, a middle region, a throat and an outlet;said middle region having a shape which defines an apex of greater cross-sectional area than that of said inlet and said throat;said inlet being curved; andthe intersecti

[ What is claimed is:] [1.]1. A rocket nozzle comprising:a nozzle member having an inlet, a middle region, a throat and an outlet;said middle region having a shape which defines an apex of greater cross-sectional area than that of said inlet and said throat;said inlet being curved; andthe intersection between said middle region and said throat being angular;whereby when combustion gases are directed toward said inlet, solid particles therein are accelerated through said inlet at an angle to the centerline thereof and are siphoned away from the throat to prevent significant impingement thereon, while the flow velocity of combustion gases near said throat is reduced from the flow velocity of solid particles near the centerline thereof.