Abstract: A gas turbine engine comprising a compressor, a power turbine, a counter-rotating compressor turbine for powering the compressor and a heat exchanger interconnected among them, uses a mixer to mix waste fluid heated by the heat exchanger with combustion air and feed the mixture to a combustor.

Abstract: A gas turbine engine comprising a turbine mounted downstream of a compressor and a heat exchanger interconnected between the turbine and compressor and to a heated fluid source, which is connected to a fuel source, has a compressor flow duct having a plurality of flow duct areas, each providing a different compression ratio, and a plurality of outlet taps, each communicating with a respective area of the plurality of flow duct areas, that supplies combustion air to the gas turbine engine flow duct and also controls an outlet tap switch having a plurality of positions for selectively opening to the atmosphere one outlet tap and disconnecting the rest of the outlet taps from the atmosphere in each switch position.

Abstract: An engine with counter-rotating rotors, which are coaxially arranged and are driven via a shaft by a turbine whose working medium is supplied by a gas generator with an air inlet, the air inlet (3) being arranged between (in the axial direction) the rotors (1, 2) in order to reduce the noise annoyance (FIG. 1), the rotors driven by an epicyclic gear, the internal gearwheel driving the rear rotor the plant carrier driving the front rotor.

Abstract: A method of operating a gas turbine engine having a compressor, a combustor between a waste fluid compressor and a power turbine, a counter-rotating compressor turbine installed downstream of the power turbine, and a heat exchanger having two circuits, in which a heated fluid is prepared by burning fuel with combustion air in a mixture with a waste fluid obtained downstream of a compressor turbine that which is cooled, compressed and heated before mixing with combustion air while keeping the temperature of the waste fluid downstream of the compressor turbine constant and removing a partial flow of the waste fluid into the atmosphere before heating the waste fluid prior to supplying the waste fluid for mixing with the combustion air.

Abstract: The present invention deals wish a turboreactor comprising at least a precombustion chamber, a combustion chamber, means for directing combustion gases from the precombustion chamber into the combustion chamber, an air compressor, and means for dividing the air flow from the Iair compressor while guiding it in the combustion chamber. The turboreactor comprises advantageously a contrarotating stator The invention relates also to a process in which the blades are heated and pushed in a thermoplastic layer of the body of the rotor and/or stator.

Abstract: A twin spool counter-rotating turbofan gas turbine engine having a counter-rotating fan module integrated with the high pressure compressor and driven by a counter-rotating turbine utilizing only two drive shafts. The two drive shafts are aerodynamically coupled and rotate in opposite directions relative to each other with or without the use of a gearbox. The integration between the fan module and high pressure compressor allows the fan blade rows to operate at the same mechanical speed of the high pressure compressor blade rows. An afterburner module may be added to the present invention to provide thrust augmentation.

Abstract: A gas turbine engine that has a turbine (1) mounted downstream of a combustor (5), a compressor turbine (2) mounted downstream of turbine (1) for producing power for driving a compressor (3), a heat exchanger (6) having a first circuit (61) connected to compressor turbine (2) and a second circuit (62) connected between compressor (2) and turbine (1) and a fluid discharge device (7) between compressor (3) and combustor (5). The gas turbine engine has a reactor (8) that has a heating device (9), inlets (F, W) connected to sources of fuel and water and an outlet connected to combustor (5). Heating device (9) is connected the outlet of compressor turbine (2). The engine also has a system for keeping the temperature at the outlet of compressor turbine (2) constant.

Abstract: In a gas turbine engine in which bearings (18, 30) of turbine (12) and compressor turbine (22) and exhaust duct (32) of compressor turbine (22) are attached to external annular wall (46) of heat exchanger (44). External annular wall (46) of heat exchanger (44) has heat insulation layer (48) on the inside surface. The engine has cooling device (94) for cooling external annular wall (46) of heat exchanger (44) on the side opposite to heat insulating layer (48).

Abstract: A twin spool counter-rotating turbofan gas turbine engine having a counter-rotating fan module integrated with the high pressure compressor and driven by a counter-rotating turbine utilizing only two drive shafts. The two drive shafts are aerodynamically coupled and rotate in opposite directions relative to each other with or without the use of a gearbox. The integration between the fan module and high pressure compressor allows the fan blade rows to operate at the same mechanical speed of the high pressure compressor blade rows. An afterburner module may be added to the present invention to provide thrust augmentation.