Abstract: A two-shaft gas turbine includes a high-pressure turbine having an annular gas-passage outlet, a low-pressure turbine having an annular gas-passage inlet, an annular intermediate duct that connects the gas-passage outlet to the gas-passage inlet, a bearing that supports a rotor of the high-pressure turbine and that is attached to a bearing case, and a plurality of struts that support the bearing case. The struts are arranged radially along the circumference of the bearing case so as to extend though the intermediate duct in a space between an outer peripheral surface of the bearing case and an inner peripheral surface of a casing wall that surrounds the intermediate duct. The intermediate duct has strut covers through which the struts extend and which function as first-stage stator blades for the low-pressure turbine.

Abstract: A gas turbine includes a cooling-air transfer system. The cooing-air transfer system extracts part of air discharged from a compressor to a chamber, and transfers the part of air as cooling air to a rotor disk. The cooling-air transfer system includes a plurality of tubular nozzles independently arranged in a circle inside the chamber to surround a rotor, and a seal disk having seal-disk cooling conduits arranged in a circle around the axis of the rotor so as to receive cooling air ejected from the tubular nozzles. The cooling-air transfer system swirls the cooling air ejected from the tubular nozzles.

Abstract: An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented.

Abstract: Bleeding is operated by annularly providing plural stationary blades at an interior side of a vehicle; annularly providing plural moving blades around rotor disk adjacent to stationary blades; providing plural stage units comprising the stationary and moving blades; introducing bleed air into each stage unit from a compressor; supplying bleed air extracted from a final stage of the compressor into a first stage unit; and supplying bleed air extracted from compressed air which has not yet arrived at a final stage unit of the compressor.

Abstract: A sealing air bypass flow path is provided in a gas turbine for supplying sealing air to a sealing air supply flow path by bypassing the flow path between each tangential on board injection (TOBI) nozzles and disk holes.

Abstract: In order to decrease gas leakage and in order to restrict the friction between the brush and the rotating shaft, a seal structure for a rotating shaft comprises a stator section, a rotating shaft, a groove, a brush, a spring member, and a connecting hole induces fluid pressure which presses the ring in a direction in which the ring approaches to the rotating shaft so as to be against the spring force of the spring member and make the brush contact the inner surface of the stator, the sealing structure prevents the fluid from flowing between the rotating shaft and the stator having a clearance from the surface of the rotating shaft and flowing in an axial direction of the rotating shaft.

Abstract: In order to provide a gas turbine and a gas bleeding method which can prevent the loss of drive power due to gas bleeding to the rotor disk, bleed gas is imparted with swirling flow in the same rotational direction as that of a first stage rotor disk by being passed through a set of TOBI nozzles which constitute a flow conduit therefor, and is supplied to this first stage rotor disk, with a portion of this bleed gas flow being bypassed and being supplied between first stage stationary blades and first stage moving blades.

Abstract: Bleeding is operated by annularly providing plural stationary blades at an interior side of a vehicle; annularly providing plural moving blades around rotor disk adjacent to stationary blades; providing plural stage units comprising the stationary and moving blades; introducing bleed air into each stage unit from a compressor; supplying bleed air extracted from a final stage of the compressor into a first stage unit; and supplying bleed air extracted from compressed air which has not yet arrived at a final stage unit of the compressor.

Abstract: A plurality of moving blades are provided around rotor disks and rotate together with said rotor disks. Compressor rear case rings surround the periphery of these moving blades and form a compression flow path therein. A bleeding chamber is provided around the compressor rear case rings and introduces a portion of a main flow moving through the compression flow path as bleed air. Cooling flow path is formed between the compressor rear case rings and the bleeding chamber in which bleed air cf on its way to the bleeding chamber flows along the outer surface of the compressor rear case rings.

Abstract: An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidization is prevented, and high temperature deformation is prevented.

Abstract: A sealing air bypass flow path is provided in a gas turbine for supplying sealing air to a sealing air supply flow path by bypassing the flow path between each tangential on board injection (TOBI) nozzles and disk holes.

Abstract: In order to decrease gas leakage and in order to restrict the friction between the brush and the rotating shaft, a seal structure for a rotating shaft comprises a stator section, a rotating shaft, a groove, a brush, a spring member, and a connecting hole induces fluid pressure which presses the ring in a direction in which the ring approaches to the rotating shaft so as to be against the spring force of the spring member and make the brush contact the inner surface of the stator, the sealing structure prevents the fluid from flowing between the rotating shaft and the stator having a clearance from the surface of the rotating shaft and flowing in an axial direction of the rotating shaft.

Abstract: A gas turbine capable of minimizing the clearance between each of the rotor blades and partition ring, uses a structure in which the upstream thermally insulating ring is installed on the downstream blade ring.

Abstract: In order to provide an axial compressor, and a gas bleeding method to the thrust balance disks thereof, which are capable of preventing reduction of the mechanical strength of the thrust balance disks due to excessive heating up by bleed gas, a portion of the fuel gas F, after having passed through the diffuser, is conducted to the thrust balance disks as the bleed gas flow c.

Abstract: In order to provide a gas turbine and a gas bleeding method which can prevent the loss of drive power due to gas bleeding to the rotor disk, bleed gas is imparted with swirling flow in the same rotational direction as that of a first stage rotor disk by being passed through a set of TOBI nozzles which constitute a flow conduit therefor, and is supplied to this first stage rotor disk, with a portion of this bleed gas flow being bypassed and being supplied between first stage stationary blades and first stage moving blades.

Abstract: A plurality of moving blades are provided around rotor disks and rotate together with said rotor disks. Compressor rear case rings surround the periphery of these moving blades and form a compression flow path therein. A bleeding chamber is provided around the compressor rear case rings and introduces a portion of a main flow moving through the compression flow path as bleed air. Cooling flow path is formed between the compressor rear case rings and the bleeding chamber in which bleed air cf on its way to the bleeding chamber flows along the outer surface of the compressor rear case rings.

Abstract: In order to provide an axial compressor, and a gas bleeding method to the thrust balance disks thereof, which are capable of preventing reduction of the mechanical strength of the thrust balance disks due to excessive heating up by bleed gas, a portion of the fuel gas F, after having passed through the diffuser, is conducted to the thrust balance disks as the bleed gas flow c.