Mitsubishi Heavy Industries Limited

Vincent Laurello

Masanori Yuri

Yasuoki Tomita

Satoshi Hada

Friedrich Soechting

Charles Ellis

Osamu Isumi

Shinichi Inoue

Hiroshige Matsuoka

Keita Fujii

Mitsuhiro Noguchi

Hada Satoshi

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. In order to achieve the object, the present invention provides a ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades comprising a plurality of individual units which define an annular form by being arranged around the peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from the tips of the moving blades, wherein grooves which extend along the axial direction of the main shaft of the turbine are formed upon of the individual units so as mutually to confront one another; a seal plate which is inserted into each mutually confronting pair of the grooves so as to connect together the adjacent pair of individual units; and contact surfaces which are formed at positions more radially inward than the seal plates, which extend in the axial direction and the peripheral direction and which mutually contact one another.

Ring segment of gas turbine

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.

Gas turbine and bleeding method thereof

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.

Gas turbine

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.

Seal structure, turbine having the same, and leak-preventing seal system for rotating shaft

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.

Gas turbine and method of bleeding gas therefrom

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.

Gas turbine compressor and clearance controlling method therefor

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.

Gas turbine having thermally insulating rings

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.

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Miami, FL, United States of America

Vincent Laurello