Abstract: Apparatus for suppressing infrared radiation emitted from hot metal parts at the aft end of a gas turbine engine and from the exhaust gas plume thereof is provided and such apparatus employs components which utilize an ejector principle to provide cooling action utilizing ambient air and such components may be provided with means for adjustment thereof to vary the amount of cooling ambient air.

Abstract: An internal combustion engine comprises a housing defining an air inlet opening, a first set of rotatably mounted interengaging air intake and compression rotor wheels, and an air passageway connecting said air intake and compression rotor wheels to a second set of rotatably mounted interengaging compression and metering rotor wheels. The compression and metering rotor wheels deliver air to a combustion chamber defined by the housing. Fuel is injected into the combustion chamber and ignited. The combustion chamber communicates with a third set of rotatably mounted interengaging output rotor wheels which are driven by the exhaust gases and are connected to drive the aforementioned rotor wheels. The working area of the output rotor wheels is greater than the working area of the compression and metering rotor wheels, wherein the combustion gases always drive the output rotor wheels.

Abstract: The invention relates to a method and a means to prevent cavitation and/or erosion in propeller ducts, and the invention is generally characterized in that air is supplied to the so-called "gap cavities" which are formed at the blade extremities or tips and between blade tips and the duct surface.

Abstract: A dual-flow or multiflow gas turbine power plant comprising a jet pipe, at east two separate flow-ducts each opening into the jet pipe, namely a first flow-ducts through which passes, in operation, a first gas flow and which contains a gas generator of the gas turbine type and an expansion-turbine located downstream of the gas generator, and a second flow-ducts through which passes, in operation, a second gas flow and a mixer device in which the first gas flow leaving the expansion turbine, and the second gas flow, are arranged to be mixed prior to entering the jet pipe, the plant further comprising a recompressor located downstream of the mixer device, in which the mixture of the two gas flows is arranged to be recompressed before entering the jet pipe.

Abstract: This invention relates to an improvement in an aircraft having a tail-mounted, shrouded pusher-type propeller and an engine mounted in front of the shroud, the improvement comprising exhaust pipe running from the engine to the shroud.

Abstract: An ejector wing, for an aircraft, having inlet and diffuser doors which move from an open take-off configuration to a closed forward flight configuration and having hypermixing nozzles and root nozzles for supplying primary air into a plurality of channels in the wing structure. Apparatus is provided for controlling the air flow from the root nozzles in the boundary layer in the channels. A plurality of sensing ports are provided in the channels upstream of the root nozzles. The differential pressures at the sensing ports are used to divide the flow to the root nozzles on opposite sides of the channels.

Abstract: A jet propulsion engine such as a gas turbine engine has an air compressor for supplying compressed air to the engine compressor stages. The air compressor is controllably and selectively driven by way of a disconnectable drive connection between the air compressor and a freely rotatable fan which is arranged in front of the air compressor and which in operation is rotated by the flow of intake air into the engine. A by-pass duct permits a part of the intake air to be by-passed around the air compressor and passed in variable proportions either to the engine compressor stages or directly out of a by-pass duct outlet.

Abstract: The purpose of this invention is a propeller capable of generating high tst at reduced noise levels, weight and drag. The propeller blades employ a tangential slot along the trailing edge of each propeller blade and circulation control blowing from the tangential slot over the trailing edge. Lift is generated by the coanda blowing. The lift is proportional to the momentum flow of the air out of the slot and is substantially independent of the rotational velocity. Additionally a circulation control shroud expands the thrusting slipstream of the propeller so that the shroud diffusion angle is increased and the average exit velocity is reduced, thereby increasing efficiency and reducing noise.