Convergent divergent jet engine nozzle

A thrusting nozzle suitable for use with jet engines, said nozzle comprising:

• a non-rotating, annular shell having a longitudinal axis with an inner wall extending generally in the direction of the longitudinal axis between an inlet and an outlet;
• and
• an inner body of revolution having a longitudinal axis, said inner body having an outer wall with an upstream end and a downstream end, said inner body being positioned within and coaxially with said annular shell with said upstream end of said outer wall being positioned adjacent to said inlet of said annular shell with said outer wall extending downstream toward said outlet of said annular shell so as to form a gas flow passageway between the outer wall of said inner body and the inner wall of said annular shell, the inner wall of said annular shell providing the outer flow boundary for the gas flow passageway and the outer wall of said inner body providing the inner flow boundary for the gas flow passageway;
• said inner wall of said annular shell and said outer wall of said inner body being shaped so as to provide an inlet zone, a throat and an outlet zone in a sequence extending from the inlet of said annular shell to the outlet of said annular shell, the inner wall of said annular shell and the outer wall of said inner body continuously and gradually converging toward each other in said inlet zone so that the cross sectional area of said gas flow passageway at said throat is smaller than the cross sectional area of said gas flow passageway at said inlet of said annular shell;
• wherein said inner body is rotatably positioned within and coaxially with said annular shell so that said inner body can be rotated about its longitudinal axis.

A jet engine comprising an engine housing having a longitudinal axis and containing an air inlet, an air diffuser, an air compressor, a combustion chamber, a gas turbine mounted on a shaft, and a thrust nozzle, said gas turbine having a turbine discharge;

• said thrust nozzle comprising:
• a non-rotating, annular shell positioned coaxially with said longitudinal axis with an inner wall extending generally in the direction of the longitudinal axis between an upstream inlet end and a downstream outlet;
• and
• an inner body having an outer wall with an upstream end and a downstream end, said inner body being positioned within and coaxially with said annular shell with said upstream end of said outer wall being positioned adjacent to said upstream inlet end of said annular shell to form a nozzle inlet with said outer wall extending downstream toward said outlet of said annular shell so as to form a gas flow passageway between the outer wall of said inner body and the inner wall of said annular shell, the inner wall of said annular shell providing the outer flow boundary for the gas flow passageway and the outer wall of said inner body providing the inner flow boundary for the gas flow passageway with the nozzle inlet being connected directly to the turbine discharge, and with the turbine discharge and the nozzle inlet having the same annular gas flow area and the aerodynamic boundaries of the turbine discharge and the nozzle inlet being continuous;
• said inner wall of said annular shell and said outer wall of said inner body being shaped so as to provide an inlet zone, a throat and an outlet zone in a sequence extending from the upstream inlet end of said annular shell to the downstream outlet of said annular shell, the inner wall of said annular shell and the outer wall of said inner body gradually and continuously converging toward each other in said inlet zone so that the cross sectional area of said gas flow passageway at said throat is smaller than the cross sectional area of said gas flow passageway at said inlet end of said annular shell and so that the cross sectional area of said gas flow passageway continuously and gradually decreases from the nozzle inlet to the throat to produce a continuous acceleration of flow of gases passing through said gas flow passageway, with a sonic velocity of the gases in the throat and a supersonic velocity of the gases at the outlet of said annular shell for gases having a sufficient pressure differential between the nozzle inlet and the outlet of said annular shell.

A jet engine comprising an engine housing having a longitudinal axis and containing an air inlet, an air diffuser, an air compressor, a combustion chamber, a gas turbine mounted on a shaft, and a thrust nozzle;

• said thrust nozzle comprising:
• a non-rotating, annular shell positioned coaxially with said longitudinal axis with an inner wall extending generally in the direction of the longitudinal axis between an upstream inlet end and a downstream outlet;
• and
• an inner body having an outer wall with an upstream end and a downstream end, said inner body being positioned within and coaxially with said annular shell with said upstream end of said outer wall being positioned adjacent to said upstream inlet end of said annular shell with said outer wall extending downstream toward said outlet of said annular shell so as to form a gas flow passageway between the outer wall of said inner body and the inner wall of said annular shell, the inner wall of said annular shell providing the outer flow boundary for the gas flow passageway and the outer wall of said inner body providing the inner flow boundary for the gas flow passageway;
• said inner wall of said annular shell and said outer wall of said inner body being shaped so as to provide an inlet zone, a throat and an outlet zone in a sequence extending from the upstream inlet end of said annular shell to the downstream outlet of said annular shell, the inner wall of said annular shell and the outer wall of said inner body gradually and continuously converging toward each other in said inlet zone so that the cross sectional area of said gas flow passageway at said throat is smaller than the cross sectional area of said gas flow passageway at said inlet end of said annular shell;
• wherein said inner body is rotatably mounted on said shaft so that said inner body can be rotated about said longitudinal axis.