Rocket engine with dual contour nozzle
AssigneeInnovative Rocket Technologies Inc.
InventorsAsad Malik, Jeffery Alan Muss
Life of this patent
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Abstract
A rocket engine includes a primary chamber and a double contour nozzle attached to the primary chamber. The double contour nozzle includes an inner contour nozzle, an outer contour nozzle, and a transition region between the inner contour nozzle. The inner contour nozzle includes a conical contour. The outer contour nozzle includes a bell contour and at least one propellant injection orifice. The contour break point includes a radius of curvature that is less than 0.75 and a tangency angle that is in a range of from 40 degrees to 90 degrees.
Claims15
A rocket engine, comprising:
- a primary chamber;
- and
- 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;
- and
- a transition region between the inner contour nozzle and the outer contour nozzle;
- wherein the transition region comprises a radius of curvature that is less than 0.75 and a tangency angle that is in a range of from 40 degrees to 90 degrees.
A rocket engine, comprising:
- a primary chamber;
- and
- a double contour nozzle attached to the primary chamber, wherein the double contour nozzle comprises
- an inner contour nozzle comprising a conical contour, and
- an outer contour nozzle comprising
- a bell contour,
- an outer contour nozzle downstream end, and
- at least one propellant injection orifice, and
- a transition region between the inner contour nozzle and the outer contour nozzle,
- wherein the outer contour nozzle further comprises an axial length extending from the transition region to the outer contour nozzle downstream end, and
- wherein the at least one propellant injection orifice is positioned downstream of the transition region from 0-15% along the axial length of the outer contour nozzle.
Dependencies are inferred from the claim text.