Abstract: An aircraft, with the ability to cruise at supersonic speeds, designed to increase cruise lift/drag ratio, reduce sonic boom and have greater downward visibility by having an ‘inverted’ nose profile that has greater inclination of the lower surfaces to the flight direction than the upper surfaces.

Abstract: A motor or generator having a rotor comprising an outer peripheral ring and having round bar permanent magnets with an axial length smaller than a diameter of the magnets embedded into the ring. The stator surrounding the motor and the stator comprising a stationary ring having a substantially flat sheet ring configuration including electrical conductors therein. The rotor comprises a flux-transfer ring rotating substantially as a unit with the outer peripheral ring. The flux transfer ring being substantially flat and facing the flat sheet ring.

Abstract: A fan for creating lift or thrust having a fan hub and fan blades depending from the fan hub. The fan blades have slots formed therein with openings facing substantially aft, relative to a rotation direction of the fan blades, wherein air blowing from the fan hub into the fan blades and out of the openings of the slots contribute to the aerodynamic performance of the fan blades to enhance the aerodynamic performance of the fan blades.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A gas turbine engine ducted to have the air pass sequentially through a single stage axial-flow compressor, a single-stage hybrid axial-radial centrifugal compressor, a burner, an inward flow radial turbine, an axial-flow, high-pressure turbine, and then exit nozzles. The axial compressor and axial turbine are on a common core shaft. The centrifugal compressor and the radial turbine are on a common porous hub and form an integral, modular unit in which forces on the radial turbine blades drive the centrifugal compressor. The porous common hub permits air to transpire from the compressor to the turbine, serving to cool the turbine. Fuel is burned in annular, "folded-comma" shaped burners with multiple fuel-injection and ignition zones (two stage combustion).

Abstract: An air compressor with porous surfaces to separate particles from air flowing therethrough, using curvilinear flow paths to effect the same.

Abstract: A gas turbine engine ducted to have the air pass sequentially through a single stage axial-flow compressor, a single-stage hybrid axial-radial centrifugal compressor, a burner, an inward flow radial turbine, an axial-flow, high-pressure turbine, and then exit nozzles. The axial compressor and axial turbine are on a common core shaft. The centrifugal compressor and the radial turbine are on a common porous hub and form an integral, modular unit in which forces on the radial turbine blades drive the centrifugal compressor. The porous common hub permits air to transpire from the compressor to the turbine, serving to cool the turbine. Fuel is burned in annular, "folded-comma" shaped burners with multiple fuel-injection and ignition zones (two stage combustion). The gas flow path has an outer annular duct, a first inner duct from the burner, and a second inner duct to the burner. The outer duct shares common walls with the first and second inner ducts.