Abstract: A gas turbine engine for an aircraft comprises a gas generator which includes a compressor stage, a combustion chamber, and a turbine for driving the compressor, and through which the air and combustion gases flow from the rear towards the front in relation to the direction of travel of the aircraft before undergoing a reversal of direction to feed two contra-rotating power turbines which directly drive two contra-rotating airscrew or fan stages located near the front of the engine in the same longitudinal region as the power turbines. The gas generator is supplied by an air intake consisting of a plurality of ducts disposed around the outer casing of the engine, and the gases exiting from the power turbines are exhausted through a plurality of ducts positioned between the inlet ducts.

Abstract: A rotor stage disposed within an annular fluid flowpath in a turbomachine is disclosed. The rotor stage includes outer and inner rings and a plurality of first and second airfoils. The outer and inner rings define flowpath surfaces for said flowpath. The first and second airfoils extend between the rings for transferring energy between the fluid and the rotor stage. At least one of the first airfoils surrounds means for transmitting energy across the flowpath.

Abstract: An improved arrangement of a turbofan engine comprises a core engine, an upstream fan, a downstream fan and a booster compressor. The upstream fan and downstream fan are both positioned upstream of the core engine, and are arranged to be driven in opposite directions by a gear assembly. The gear assembly is positioned axially between the upstream fan and downstream fan. The booster compressor is positioned upstream of the upstream fan and downstream fan, and comprises a first rotor carrying blades and a second rotor carrying blades. The first rotor is driven with the upstream fan and the second rotor is driven by the turbine of the core engine in opposite direction to the first rotor.

Abstract: A turbojet having a multistage axial compressor with contrarotating blade wheels fitted on inner and outer contrarotating rotors driven in opposite directions by respective turbine wheels.Each blade wheel (105) of the outer compressor rotor is associated with a rotating shell (86, 81, 82) having relatively few thick spokes for transmitting the drive from the turbine wheel, thereby leaving the blades to transmit aerodynamically induced forces only.

Abstract: A gas turbine power plant has a compressor stage and a turbine stage with an annular combustion stage therebetween. Each of the contra-rotatable compressor rotors is connected to one of the contra-rotatable turbine rotors by an elongated hollow cylindrical shaft concentric with an axially extending fixed shaft to form an integral unit. The units are operably connected by differential gearing mounted on the fixed shaft just in rear of the nose of the engine at the air intake end of the housing.

Abstract: A ducted fan gas turbine engine comprises a pair of turbines in flow series which are contra-rotating and which drive shafts which in turn drive into an epicyclic gear. The output from the epicyclic gear drives a fan which normally provides forward thrust from the engine. The fan can be made to rotate in the opposite direction to provide reverse thrust by varying the relative speeds of rotation of the two turbines by bleeding working fluid from between them.