Patent ID: 11952967
Assignee: SIERRA SPACE CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 5:
6. A method of a vortex hybrid motor, comprising:
delivering, from a first injector of a first angled injector unit positioned along an injector ring, a first stream of a liquid propellant into a combustion chamber housing of the vortex hybrid motor, the first stream being directed at a first impingement point;
delivering, from a second injector of the first angled injector unit positioned along of the injector ring, a second stream of the liquid propellant into the combustion chamber housing, the second stream being directed at the impingement point;
delivering, from a third injector of a second angled injector unit positioned along the injector ring, a third stream of a liquid propellant into the combustion chamber housing of the vortex hybrid motor, the third stream being directed at a second impingement point; and
delivering, from a fourth injector of the second angled injector unit positioned along the injector ring, a fourth stream of the liquid propellant into the combustion chamber housing, the fourth stream being directed at the second impingement point,
wherein the first angled injector unit comprises the first injector and the second injector extending along a vertical plane that is parallel to a longitudinal axis of the combustion chamber housing, the second angled injector unit comprising the third injector and the fourth injector extending along a horizontal plane that is transverse to the longitudinal axis of the combustion chamber housing, and the first angled injector unit and the second angled injector unit alternating along a length of the circular body of the injector,
wherein the first stream and the second stream collide at the first impingement point to thereby atomize the liquid propellant and form a first spray fan formation along a first injection plane, and
wherein the third stream and the fourth stream collide at the second impingement point to thereby atomize the liquid propellant and form a second spray fan formation along a second injection plane.