Combustor

A combustor for a jet engine, said jet engine having a compressor portion and a turbine portion, the combustor comprising:

• a) an outer tube having a central axis, said outer tube extending longitudinally and positioned to receive air discharged by said compressor portion and said outer tube having an outer surface and an inner surface;
• b) an inner tube positioned within said outer tube, said inner tube having an outer surface spaced from said inner surface of said outer tube, thereby defining a combustion chamber passage therebetween;
• c) said outer tube including fluid directing structure for communicating at least some of the air discharged by said compressor portion into said combustion chamber passage, said air being directed in a direction offset from said central axis, thereby causing rotation of said air about said central axis;
• d) at least one fuel supply member for supplying a fuel to said combustion chamber passage in order to form a rotating fuel air mixture in said combustion chamber passage.

A combustor for a jet engine, said jet engine having a compressor portion and a turbine portion, the combustor comprising:

• a) a tube having a central axis, the tube being located intermediate said compressor portion and said turbine portion, said tube having an outer surface and an inner surface;
• b) fluid directing structure formed on said tube including passages extending from said outer surface to said inner surface;
• c) said inner surface of said tube defining a combustion chamber;
• d) a passage communicating air discharged by said compressor portion with said outer surface of said tube for delivering compressor air to said combustion chamber through said fluid directing structure, said fluid directing structure directing said compressor air at an angle offset from said central axis, thereby causing rotation of said compressor air in said combustion chamber;
• e) a fuel member for supplying fuel to said combustion chamber.

A method for combusting fuel in a jet engine having compressor and turbine portions, comprising the steps of:

• a) providing a tube having an outer surface communicating with air discharged by said compressor portion and an inner surface at least partially defining a combustion chamber;
• b) providing fluid directing structure between said inner and outer surfaces for communicating said compressor air from said outer surface to said combustion chamber, at an angle offset with respect to a central axis of said tube, such that said air is caused to rotate within said combustion chamber;
• c) supplying fuel to said combustion chamber to thereby provide a swirling fuel/air mixture;
• d) at least partially combusting said fuel air mixture in said combustion chamber;
• e) supplying said combusted fuel/air mixture to said turbine portion.