Rocket engine with dual contour nozzle
AssigneeInnovative Rocket Technologies Inc.
InventorsAsad Malik, Jeffery Alan Muss
Life of this patent
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Abstract
Some embodiments of the present disclosure are directed to a rocket engine, comprising a primary chamber and a double contour nozzle attached to the primary chamber. In some embodiments, the double contour nozzle comprises an inner contour nozzle comprising a conical contour; an outer contour nozzle comprising a bell contour and at least one propellant injection orifice; and a contour break point between the inner contour nozzle and the outer contour nozzle. Ins some embodiments, the outer contour nozzle comprises a radius of curvature of less than 0.75 and a tangency angle of 40 to 90 degrees on a surface adjacent to the contour break point.
Claims18
A rocket engine, comprising:
- a primary chamber;
- a double contour nozzle attached to the primary chamber, wherein the double contour nozzle comprises
- an inner contour nozzle comprising a conical contour;
- an outer contour nozzle comprising
- a bell contour, and
- at least one propellant injection orifice,
- wherein the at least one propellant injection orifice is configured to receive propellant injected therein using a pressure fed power cycle, an electric pump power cycle, a gas generator power cycle, a staged power cycle, a full flow staged power cycle, and expander power cycle, a combustion tap-off power cycle, or any combination thereof;
- and
- a contour break point between the inner contour nozzle and the outer contour nozzle;
- wherein the outer contour nozzle comprises a radius of curvature of less than 0.75 and a tangency angle of 40 to 75 degrees on a surface adjacent to the contour break point.
A rocket engine, comprising:
- a primary chamber;
- a double contour nozzle attached to the primary chamber, wherein the double contour nozzle comprises
- an inner contour nozzle comprising a conical contour,
- an outer contour nozzle comprising
- a bell contour,
- an outer contour nozzle exit, and
- at least one propellant injection orifice,
- wherein the at least one propellant injection orifice is configured to receive propellant injected therein using a pressure fed power cycle, an electric pump power cycle, a gas generator power cycle, a staged power cycle, a full flow staged power cycle, and expander power cycle, a combustion tap-off power cycle, or any combination thereof, and
- a contour break point between the inner contour nozzle and the outer contour nozzle,
- wherein the outer contour nozzle further comprises an axial length extending from the contour break point to the outer contour nozzle exit, and
- wherein the at least one propellant injection orifice is positioned downstream of the contour break point from 0-15% along the axial length of the outer contour nozzle.
Dependencies are inferred from the claim text.