Patent ID: 7891166

Claim:
A water rocket engine with a two-phase nozzle, comprising: a reservoir, and a nozzle assembly disposed along a central longitudinal axis therein, wherein the reservoir has an upper portion and a lower portion, the upper portion thereof being adapted for receiving a volume of pressurized air, the lower portion thereof being adapted for receiving a volume of liquid water; the nozzle assembly comprising an inverted cup shaped fluid capture vessel concentrically extending from an elongated tube, the inverted cup shaped fluid capture vessel being positioned within the lower portion of the reservoir and being completely submerged within the volume of liquid water stored therein, the inverted cup shaped fluid capture vessel having an open lower end for receiving the water and a closed upper end, the closed upper end being secured to an outer surface of the elongated tube such that the elongated tube is positioned co-axially therewith; the elongated tube having a sidewall that forms a nozzle gas inlet at an upper portion of the tube, a nozzle outlet at a lower portion of the tube, and a passageway disposed between the tube upper portion and the tube lower portion, wherein the nozzle gas inlet is positioned within the upper portion of the reservoir such that the pressurized air flows into the nozzle gas inlet, through the passageway and out of the nozzle outlet; within the confines of the capture vessel, a plurality of fluid injection holes are disposed in the sidewall of the elongated tube, wherein the plurality of fluid injection holes are arrayed along the sidewall within a central region thereof which is covered and surrounded by the inverted cup shaped fluid capture vessel; and wherein the water captured in the inverted cup shaped capture vessel flows through the plurality of fluid injection holes to combine with the air flowing through the tube inlet to thereby form a combined fluid-gas propellant that accelerates through the passageway and is expelled from the nozzle outlet to provide increased thrust of the rocket engine.