Patent ID: 6668539
Filing Date: 2003-12-30
Classification: F01D,F02C,Y02T

Abstract:
A jet-propelled rotary engine comprising:a stator; a rotor operatively coupled to the stator for rotation of the rotor relative to the stator about a rotor axis, the rotor comprising at least first and second jet assemblies, the first and second jet assemblies being adapted to traverse a circular path as the rotor rotates about the rotor axis, the first jet assembly defining a first converging flow region, a first diverging flow region downstream of the first converging flow region, and a first discharge port, the second jet assembly defining a second converging flow region, a second diverging flow region downstream of the second converging flow region, and a second discharge port; a combustion region having an upstream portion, the rotary engine being adapted to cause a combustion reaction of an oxygen-fuel mixture in the combustion region in a manner to form combustion reaction products which comprise at least a part of thrust matter to be discharged through the discharge ports of the first and second jet assemblies, the rotary engine being adapted to combust at least some of the oxygen-fuel mixture in the upstream portion of the combustion region such that at least a portion of the combustion reaction occurs in the upstream portion of the combustion region, the rotary engine being adapted and configured to channel at least some of the thrust matter formed in the upstream portion of the combustion region through the discharge ports of the first and second jet assemblies and adapted to discharge the thrust matter from the discharge port of the first and second jet assemblies at a supersonic velocity; and a generally annular duct circumscribing the circular path, the duct having an annular diverging region, the diverging region of the duct diverging radially outwardly.