Abstract: A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base portion, an external airfoil surface, a blade flow portion of the airfoil, and a passage system communicating with the compressor and with the blade flow portion to create a thermal insulating boundary between the heated fluid and the external airfoil surface. The rotor has a substantially planar platform member, extending substantially transversally to the body of the blade and having an upstream portion protruding in the direction toward the combustion zone. The platform member has at least a pair of openings on either side of the airfoil, the openings being positioned in series along the blade flow portion. One opening of the pair defines an inclined passage in the platform member, and the other opening is separated by a partition from the first opening.

Abstract: A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base portion, an external airfoil surface, a blade flow portion of the airfoil, and a passage system communicating with the compressor and with the blade flow portion to create a thermal insulating boundary between the heated fluid and the external airfoil surface. The rotor has a substantially planar platform member, extending substantially transversally to the body of the blade and having an upstream portion protruding in the direction toward the combustion zone. The platform member has at least a pair of openings on either side of the airfoil, the openings being positioned in series along the blade flow portion. One opening of the pair defines an inclined passage in the platform member, and the other opening is separated by a partition from the first opening.

Abstract: A gas turbine engine a turbine, a compressor turbine mounted downstream the turbine for rotation in a direction opposite to the rotation direction of the turbine that is mounted downstream the compressor. Exhaust fluid from the compressor turbine is cooled in a heat exchanger with a compressed fluid downstream the compressor and is then cooled with air in separate heat exchanger before being admitted to the compressor. A part of the compressed fluid heated in the heat exchanger is fed to cool the turbine blades, and the rest of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor and is discharged from the engine. The booster compressor is driven by an expanding turbine that rotated under the effect of combustion air that is expanded in the expanding turbine and flows through the expanding turbine under the action of reduced pressure in the heated fluid source.

Abstract: A method of operating a gas turbine engine comprising a power turbine mounted downstream a compressor, and a compressor turbine mounted downstream the power turbine for rotation in a direction opposite to the rotation direction of the power turbine. Exhaust fluid from the compressor turbine is cooled in a heat exchanger with a compressed fluid downstream the compressor and is then cooled with air in separate heat exchanger before being admitted to the compressor. A part of the compressed fluid heated in the heat exchanger is fed to cool the turbine blades, and the rest of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor and is discharged from the engine. The booster compressor is driven by an expanding turbine that rotated under the effect of combustion air that is expanded in the expanding turbine and flows through the expanding turbine under the action of reduced pressure in the heated fluid source.

Abstract: A gas turbine engine has a device for admitting a rotating fluid flow from an annular space of the casing to the inlet portion of a combustor to form a rotating fluid flow in the inlet portion of the combustor. The rotating fluid flow is formed in the annular space of the casing by supplying a fluid from a compressor to the blades of the turbine rotor disk.

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 method of operation of a gas turbine engine having a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a compressed fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.

Abstract: A gas turbine engine has a compressor, a combustor mounted downstream of the compressor, power turbine mounted downstream of the combustor, a counter-rotating compressor turbine having a temperature sensor at its outlet, a temperature control system for controlling the temperature at the outlet of the compressor turbine, and a fuel supply control system for supplying fuel to the combustor. The engine has a drive motor for causing the compressor to rotate and a motor control system having a motor power-up module with an input connected to the fuel supply control system, and a motor power output control module having a first input connected to the motor power-up module, a second input connected to the temperature sensor, and an output which is connected to the drive motor.

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: 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: A gas turbine engine has a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.

Abstract: In a gas turbine engine bladed disk (36) positioned between rotor disk (14) and combustor (16). Bladed disk (36) is mounted for rotation together with rotor disk (14) and has blades (38) projecting toward inlet portion (20) of combustor (16). The bladed disk has openings (40) between blades (38) for establishing communication between source of compressed fluid (12) and turbine blades (15). Seals (46, 48) are provided between bladed disk (36) and casing (10).

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 gas turbine engine has a turbine mounted downstream of a compressor and a compressor turbine mounted downstream of the turbine for driving the compressor. The compressor turbine has a rotor disk that is mechanically coupled to the compressor and rotates in a direction opposite to the direction of rotation of the turbine rotor disk. A heat exchanger has a first circuit connected to the compressor turbine and a second circuit connected between the compressor and the turbine. An electric load for taking off a fraction of power produced by the compressor turbine includes an electric generator that is mechanically coupled to the compressor turbine. An electric load controller changes the fraction of power produced by the compressor turbine based on readings from the temperature sensor located in the engine.