Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Power, Ltd.

Kasai Kogyo Co., Ltd.

Sony Corporation

Japan Display West Inc.

Shinya Hashimoto

Kenichi Arase

Keita Takamura

Takuro Kameda

Tetsuya Shimmyo

Masanori Yuri

Eiichi Tsutsumi

Tsutomu Harada

Mitsuru Tateuchi

Ryoichi Tsuzaki

Kazuharu Hirokawa

Masahiro Murata

Yasunori Nishioka

Norihiko Nagai

Yoshimasa Takaoka

Naoki Ikushima

Koji Watanabe

Hiroaki Kobayashi

Kazunori Yamaguchi

Naoya Okada

Takahiro Kondo

Masato Araki

Yoshio Fukui

Ryosuke Mito

Kenta Nakamura

Naoki Taketa

Takayoshi Iijima

Takeshi Umehara

Chiaki Kon

Tadashi Maekawa

Hiroki Komatsuzaki

Yoshiharu Nakajima

Hiroyuki Kojima

Hiroyuki Yamazaki

Kenta Taniguchi

Keisuke Matsuyama

Hitoshi Morimoto

Shunsuke Torii

Ryotaro Magoshi

Kenji Sato

Junichiro Masada

Yukihiro Hashimoto

Yasuro Sakamoto

Norihiko Motoyama

Go Yamanaka

Masahiko Hara

Kouichi Akagi

Kentaro Tokuyama

Kunihiko Waki

Tadao Yashiki

Hidetaka Okui

Naoya Tatsumi

Yoshiyuki Okabe

Yoshifumi Tsuji

Shingo Yamasue

Yasuhiro Ojiro

Takuro Hashimoto

Kazuki Kitagawa

Kota Yoshino

Akihiro Murakami

Yuji Komagome

Masahito Kataoka

Toyokazu Endo

Yuki Sugawara

Norikazu Tezuka

Kazunori Yamguchi

Takaya Koda

Akinori Tanitsuji

Sumiaki Tanaka

Noriyuki Koike

An exhaust system includes, a first outer diffuser, a second outer diffuser, an exhaust casing covering an outer circumferential side of the first outer diffuser, an exhaust chamber covering an outer side of the second outer diffuser, a first annular seal device, a second annular seal device, and a third annular seal device. The first annular seal device is disposed to suppress an inflow of an exhaust gas into a space between the first outer diffuser and the exhaust casing, and the second annular seal device is disposed to suppress an inflow of the exhaust gas into a space between the second outer diffuser and the exhaust chamber. The third annular seal device is disposed between the first annular seal device and the second annular seal device, and is disposed to suppress a flow of the exhaust gas to a side of the first annular seal device.

Exhaust system and gas turbine equipped with same

A blade ring assembly including: a turbine blade ring extending in a circumferential direction about an axis; a component to be cooled, disposed on an inner circumferential side of the turbine blade ring; and an outer circumferential side component disposed on an outer circumferential side of the turbine blade ring. The turbine blade ring has a cooling medium intake port leading from an outer circumferential surface to an inner circumferential surface of the turbine blade ring. The outer circumferential side component includes: a first wall portion which covers at least a portion of the cooling medium intake port from the outer circumferential side of the turbine blade ring; and a second wall portion which extends from an end portion of the first wall portion on the axially downstream thereof toward the outer circumferential side of the turbine blade ring.

Blade ring assembly, gas turbine, and method for refurbishing gas turbine

A rotor disc has diametrically outer surfaces, a diametrically inner surface, a plurality of blade root grooves recessed diametrically inward from the diametrically outer surfaces and aligned in a circumferential direction, and a plurality of hole groups formed in each of the plurality of blade root grooves and aligned in the circumferential direction. Each of the plurality of hole groups has a hole including a cooling orifice penetrating from the diametrically inner surface through to the diametrically outer surface. The width of each of the plurality of hole groups in the circumferential direction is greater than the width of each of the plurality of hole groups in an axial direction and smaller than a minimum gap among gaps between the plurality of hole groups in the circumferential direction.

Rotor disc, rotor shaft, turbine rotor, and gas turbine

A fuel supply pipe assembly according to at least one embodiment of the present disclosure is a fuel supply pipe assembly for supplying fuel to a fuel nozzle provided on a side portion of a combustion liner of a gas turbine combustor, provided with: a fuel supply pipe for supplying the fuel to the fuel nozzle; a first flange portion capable of coupling with a flange portion of a fuel line for supplying the fuel to the fuel supply pipe; and a second flange portion capable of coupling with a top hat portion of the gas turbine combustor. The first flange portion has a plurality of radially outward protrusions arranged at intervals in the circumferential direction, and a plurality of first bolt holes penetrating the first flange portion in the axial direction. The first bolt holes are formed at the same circumferential positions as the protrusions, respectively.

Fuel supply pipe assembly, gas turbine combustor, and gas turbine

The present invention includes a flow guide () that is disposed in a space (A) formed in a casing, on an outlet side of a diffuser (), the flow guide including: a first guide surface () that is disposed on a rotor side provided to a compressor and a gas turbine, and that delays turning of a flow direction of a compressed gas which has passed through the diffuser (); and a second guide surface () that is disposed outside the first guide surface () and that turns the flow direction of the compressed gas which has passed through the diffuser ().

Gas turbine

A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate in a radial direction of the rotor disc. The method includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction via a clearance between a platform of a blade and a region of an outer peripheral surface of the rotor disc except a blade groove for receiving the blade to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction.

Method for disassembling/assembling gas turbine, gas turbine rotor, and gas turbine

A first-stage stator vane for a gas turbine includes: a first portion partially defining an airfoil which includes a pressure surface, a suction surface, and a trailing edge; and a second portion positioned at a leading-edge side of the airfoil with respect to the first portion, the second portion having a recess portion or a protruding portion. The recess portion or the protruding portion has a pair of side wall surfaces, and an angle formed between the pair of side wall surfaces is less than 90 angular degrees.

First-stage stator vane for gas turbine, gas turbine, stator vane unit for gas turbine, and combustor assembly

In a gas turbine, a plurality of blade ring parts each include a plurality of first cooling flow passages, a plurality of second cooling flow passages, and a return flow passage. The first cooling flow passages are disposed on the outer side in a radial direction centering on a rotation axis, extend in an axial direction, and are disposed aligned in an axial rotation direction. The second cooling flow passages are disposed on an inner side in the radial direction with respect to the first cooling flow passages, extend in the axial direction, and are disposed aligned in the axial rotation direction. The return flow passage connects end parts of each of the first cooling flow passages and the second cooling flow passages on the same side in the axial direction with each other.

Gas turbine and method for blade ring production method

An axial-direction passage, a forced vortex passage, a first blade array passage, and a second blade array passage are formed in a rotor shaft of a turbine. Cooling air from an air extraction port of a compressor flows through the axial-direction passage which extends in an axial direction. The forced vortex passage is connected to the axial-direction passage and extends outwards in the radial direction relative to an axial line from a connecting portion between the forced vortex passage and the axial-direction passage. The first blade array passage is connected to an end portion on the outer side in the radial direction of the forced vortex passage and guides cooling air to a first blade row among a plurality of blade rows. The second blade array passage is connected to an end portion of the forced vortex passage and guides cooling air to a second blade row.

A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate relative to the rotor disc in a radial direction of the rotor disc includes a seal-plate-restraint-state switching step of moving the seal plate restraint part along the axial direction to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction from the seal plate and thereby restricts movement of the seal plate in the radial direction.

Method for disassembling/assembling gas turbine, seal plate assembly, and gas turbine rotor

A lifting beam for suspending an object to be lifted in a vertical direction has a lower end surface extending in a longitudinal direction of the lifting beam on a vertical lower side in a state where the object is suspended. The lower end surface includes a first lower end portion, a second lower end portion positioned away from the first lower end portion to a first side in the longitudinal direction, and a third lower end portion positioned away from the first lower end portion to a second side in the longitudinal direction, on the opposite side of the first lower end portion from the second lower end portion. The second lower end portion is positioned higher than the first lower end portion, and the third lower end portion is positioned lower than the second lower end portion when the object is suspended from the lifting beam.

Lifting beam and method for lifting object suspended vertically from lifting beam

A gas turbine exhaust casing includes a tubular casing wall, a bearing box housed in the casing wall, a diffuser portion forming an annular exhaust gas flow passage between the casing wall and the bearing box, a plurality of struts disposed at intervals in a circumferential direction of the casing wall, and coupling the casing wall and the bearing box, and a plurality of fastening bolts disposed on the casing wall. The casing wall includes an upper half casing forming an upper half of the casing wall and a lower half casing forming a lower half of the casing wall. The plurality of fastening bolts fasten the upper half casing and the lower half casing. The plurality of struts include a penetrated strut which has an end penetrated by at least one fastening bolt of the plurality of fastening bolts.

Gas turbine exhaust casing and gas turbine

A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate relative to the rotor disc in a radial direction of the rotor disc includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes toward the second side in the axial direction from the seal plate and thereby restricts movement of the seal plate in the radial direction.

A gas turbine is provided with an exhaust diffuser in which an exhaust flow path for circulating exhaust gas from a turbine is formed, and a cooling device for cooling a structure facing the exhaust flow path in the exhaust diffuser. The cooling device has a guide part in which a guide flow path for circulating a cooling medium is formed and which is configured to guide the cooling medium to the structure, and a switching part able to switch between a first state where a flow rate of the cooling medium flowing through the guide flow path is a first flow rate corresponding to a flow rate during a rated operation and a second state where the flow rate of the cooling medium is a second flow rate higher than the first flow rate.

Gas turbine and gas turbine operating method

Growing community of inventors

Yokohama, Japan

Shinya Hashimoto