Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Susumu Wakazono

Satoshi Hada

Eisaku Ito

Keita Takamura

Yasuro Sakamoto

Yasuo Miyahisa

Masayoshi Hatta

Takashi Fujii

Masanori Yuri

Koichi Ishizaka

Hiroyuki Otomo

Takashi Hiyama

Yukinori Machida

Kohei Hidaka

Kazuki Morimoto

Scott Cloyd

Kouichi Ishizaka

Ronald Takahashi

Kazuya Nishimura

Kotaro Miyauchi

Kentaro Tokuyama

Hiroaki Kishida

Hiroshi Kawasaki

Daigo Fujimura

Kazuhisa Tamura

Ryuta Ito

Yuya Fukunaga

Hitoshi Kitagawa

Yosuke Mukai

Hiroyuki Sakaki

Yoshifumi Tsuji

Tomohiko Yamamoto

Toshihiro Takeda

Takaaki Oda

Hiroyuki Kishihara

Santo Scimeca

Yuta Hitomi

Bob Provitola

Brandon Ruiz

A turbine stator vane according to at least one embodiment of the present disclosure comprises an airfoil, an inner shroud provided on the inner-peripheral side of the airfoil, and an outer shroud provided on the outer-peripheral side of the airfoil. The inner shroud has a first recess formed in the surface on the side opposite the airfoil across a gas path surface of the inner shroud. The outer shroud has a second recess formed in the surface on the side opposite the airfoil across a gas path surface of the outer shroud, and at least one outer passage that communicates with the second recess and does not communicate with the space inside the airfoil. The number of outer passages is greater than the number of inner passages that communicate with the first recess in the inner shroud and do not communicate with the space inside the airfoil.

Turbine stator vane

A rotor blade including: a blade body extending in a blade height direction that is a direction perpendicular to an airfoil cross-section; and a platform provided to an end at a hub side, from between a tip side and the hub side which are of the blade height direction. The blade body includes: an anterior edge and a posterior edge; a ventral surface and a dorsal surface linking the anterior edge and the posterior edge together; and a cooling passage extending in the blade height direction between the ventral surface and the dorsal surface. The ventral/dorsal wall thickness ratio at any position between the hub-side position and the middle position in the cooling passage is smaller than the ventral/dorsal wall thickness ratio at any position between the middle position and the tip-side position.

Rotor blade and gas turbine provided therewith

A stator vane assembly of a gas turbine includes: a stationary member formed to have an annular shape; and a plurality of stator vane segments each including a shroud and a vane body, the plurality of stator vane segments disposed along a circumferential direction of the stationary member at a radially inner side of the stationary member such that a cavity is disposed between the shrouds and the stationary member and the shrouds are disposed adjacent to one another in the circumferential direction of the stationary member. The stationary member has a hole which penetrates through the stationary member from a radially outer side toward the radially inner side, and a center axis of the hole is oriented toward a circumferential-direction end portion of the shroud.

Stator vane assembly of gas turbine, stationary member segment, and method of producing stator vane assembly of gas turbine

A control device includes a suction amount controller and a bleed flow controller. When an actual output is in a second output range from a second output to a third output less than the second output, the suction amount controller controls a suction amount so that the suction amount becomes constant even if the actual output decreases. The bleed flow controller controls a bleed flow so that the bleed flow gradually increases as the actual output decreases.

Gas turbine control method, storage medium storing gas turbine control program, gas turbine control device, and gas turbine facility

In a clearance control system for a gas turbine, a control device operates an adjustment device such that a first flow rate is greater than a second flow rate when a load stable state is entered in which a fluctuation range of a load shifts within a preset range, and operates the adjustment device such that the second flow rate is greater than the first flow rate when a load fluctuation state is entered in which the load falls outside the range.

Clearance control system for gas turbine

To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.

Turbine blade, manufacturing method for turbine blade, and gas turbine

A turbine blade and a gas turbine are provided with: an airfoil portion () internally including a cooling air passage (); a platform () provided in a blade base end portion () in a blade height direction (Dh) of the airfoil portion (); and a fillet portion () provided around the entire perimeter of a connecting portion of the airfoil portion () and the platform (). The fillet portion () includes a first fillet portion () which is provided on a rear side blade surface () side of the airfoil portion (), on the trailing edge () side of a position at which the distance between the rear side blade surface () of the airfoil portion () and a rear side edge portion () of the platform () is shortest, and which has a fillet width (W) that is greater than the fillet width W of other regions of the fillet portion ().

Turbine blade and gas turbine

A turbine blade includes an airfoil body, and a plurality of cooling passages extending along a blade height direction inside the airfoil body and being in communication with each other to define a serpentine flow passage. The plurality of cooling passages include first turbulators on an inner wall surface of an upstream cooling passage of the plurality of cooling passages, and second turbulators on an inner wall surface of a downstream cooling passage of the plurality of cooling passages. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the downstream cooling passage is smaller than a first angle formed by the first turbulators with respect to the flow direction of the cooling fluid in the upstream cooling passage.

A turbine rotor blade includes a blade body including a pressure-side blade wall and a suction-side blade wall. The blade body includes: a serpentine passage composed of a cooling passage separated into a plurality of parts by a partition wall that connects the pressure-side blade wall and the suction-side blade wall and extends along a height direction of the blade body; and a first cooling hole communicating at one end with the cooling passage via a first inlet opening formed in an inner wall surface of the pressure-side blade wall or the suction-side blade wall, and communicating at another end with a first outlet opening formed in an outer wall surface of the pressure-side blade wall or the suction-side blade wall of the blade body. The first cooling hole extends in a leading edge direction from the first inlet opening to the first outlet opening.

Turbine rotor blade and gas turbine

A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up&#x3c;d_mid&#x3c;d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.

A turbine blade includes: an airfoil body; a cooling passage extending along a blade height direction inside the airfoil body; and a plurality of turbulators disposed on an inner wall surface of the cooling passage and arranged along the cooling passage. The airfoil body has a first end portion and a second end portion which are opposite end portions in the blade height direction. A passage width of the cooling passage in a suction-pressure direction of the airfoil body at the second end portion is greater than a passage width of the cooling passage at the first end portion. A height of the plurality of turbulators increases from a first end portion side to a second end portion side in the blade height direction.

A turbine blade includes a blade body in which a suction side () facing one side in a circumferential direction and a pressure side () facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

Turbine moving blade and gas turbine

A first-stage stationary vane of a gas turbine includes: a vane portion including a pressure surface and a suction surface; a shroud wall portion which connects to an end portion of the vane portion and which forms a flow passage wall; a pressure-surface side fillet portion disposed on a corner portion formed by the pressure surface and a wall surface of the shroud wall portion; and a suction-surface side fillet portion disposed on a corner portion formed by the suction surface and the wall surface of the shroud wall portion. The pressure-surface side fillet portion and the suction-surface side fillet portion are separated at a leading-edge side of the vane portion so as not to connect to each other.

First-stage stationary vane of gas turbine and gas turbine

A gas turbine provided with an air bleeder tube () that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (), wherein the air bleeder tube () is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.

Gas turbine with an air bleeder tube

An exhaust-side journal bearing for supporting a gas turbine rotor is disposed inside a bearing box. The bearing box is supported by a strut which extends inward from an exhaust casing, and a seal ring having an annular inner peripheral end is disposed on the bearing box. Executed during a maintenance work are: a bearing adjustment step of displacing a bearing surface of the journal bearing relative to the bearing box in a perpendicular direction perpendicular to the axial direction; and a seal ring adjustment step of displacing the inner peripheral end of the seal ring relative to the bearing box in accordance with the direction of displacement and the amount of displacement of the bearing surface.

Growing community of inventors

Yokohama, Japan

Susumu Wakazono