Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Kentaro Tokuyama

Hiroaki Kishida

Kenta Taniguchi

Kenji Sato

Taiki Kinoshita

Hiroyuki Sakaki

Keisuke Matsuyama

Takayoshi Takashima

Hiroki Shibata

Shinji Akamatsu

Satoshi Takiguchi

Shunsuke Torii

Tetsuya Shimmyo

Akihiro Murakami

Toshinobu Ohara

Yusuke Tanaka

Shinya Hashimoto

Masaki Ono

Tetsu Konishi

Susumu Wakazono

Koichiro Iida

Kotaro Miyauchi

Takashi Hiyama

Hitoshi Kitagawa

Kenichi Hashimoto

Scott Cloyd

Kohei Hidaka

Yuta Hitomi

Bob Provitola

Brandon Ruiz

Takaya Koda

Kazuhiro Tominaga

An acoustic device for a gas turbine combustor includes: a first region positioned at a downstream side of a combustion cylinder, the first region existing at a position which is at least one of a pair of positions across the combustion cylinder in a radial direction of the combustion cylinder; a pair of second regions whose axial-direction position with respect to the combustion cylinder overlaps at least partially with the pair of positions, and whose circumferential-direction position with respect to the combustion cylinder is different from that of the pair of positions, the pair of second regions existing at positions across the combustion cylinder in the radial direction; and a third region positioned at an upstream side of the first region and the second region with respect to the combustion cylinder.

Gas turbine combustor, gas turbine, and gas turbine assembling method

A perforated plate for a gas turbine combustor according to at least one embodiment is a perforated plate provided between a combustor basket and a combustor casing of the gas turbine combustor and fixed to an outer peripheral portion of the combustor basket. In a hole arrangement area with a plurality of through holes of the perforated plate, a region close to the combustor basket has a larger average value of a ligament ratio than a region close to the combustor casing, where the ligament ratio is obtained by dividing a distance between outer peripheral edges of two adjacent holes of the plurality of through holes by a distance between centers of the two holes.

Perforated plate for gas turbine combustor, gas turbine combustor, and gas turbine

A sealing member that forms a combustion gas flow path of a gas turbine includes a first body portion having a cooling passage. The first body portion includes a first end portion forming one end portion in a circumferential direction, a second end portion forming the other end portion on an opposite side in the circumferential direction, and an intermediate portion formed between the first and second end portions. The cooling passage includes an intermediate portion cooling passage inclined at a first angle with respect to an axial direction, a first end portion cooling passage provided in the first end portion and inclined at a second angle with respect to the axial direction, and a second end portion cooling passage provided in the second end portion and inclined at a third angle with respect to the axial direction, and the second and third angles are smaller than the first angle.

Sealing member and gas turbine

This exit seal is for connecting an exit flange of a combustor and a shroud in a stator blade of a turbine. The exit seal is equipped with: a seal body that extends in a circumferential direction; and a lid member disposed at a circumferential end of the seal body. The seal body comprises one or more recessed sections that are recessed in a radial direction or in an axial direction and extend in the circumferential direction. At a position of the circumferential end of at least one recessed section among the one or more recessed sections, the lid member is disposed so as to overlap, in the axial direction and the radial direction, with a recessed space formed by the one recessed section.

Exit seal and gas turbine equipped with same

A combustion tube for a gas turbine including an outlet section having a cross-section of an annular sector-shape. The outlet section includes an outer wall forming an outer peripheral boundary of the annular sector-shape, an inner wall forming an inner peripheral boundary of the annular sector-shape, and a pair of side walls forming boundaries on both sides of the annular sector-shape in a circumferential direction, respectively. The outer wall extends obliquely with respect to the inner wall such that a height of the annular sector-shape decreases toward an outlet opening of the combustion tube. A first side wall extends obliquely with respect to a second side such that a perimeter of the annular sector-shape increases toward the outlet opening of the combustion tube. An inclination angle &#x3b8;of the first side wall with respect to the second side wall satisfies 0&#x3c;&#x3b8;&#x2264;56.

Combustion tube and combustor for gas turbine, and gas turbine

A combustor component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.

Combustor component, combustor, gas turbine, and manufacturing method for combustor component

A plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

Transition piece, combustor provided with same, and gas turbine provided with combustor

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

A gas turbine includes a plurality of first-stage stator vanes arranged in a circumferential direction, the first-stage stator vanes each including a vane surface having a pressure surface and a suction surface, a first combustor disposed on a suction surface side of one of the first-stage stator vanes, the first combustor having a first combustor outlet which includes a first side wall portion extending along a radial direction, and a second combustor disposed on a pressure surface side of the one of the first-stage stator vanes and adjacent to the first combustor in the circumferential direction. The one of the first-stage stator vanes satisfies 0.05&#x2264;&#x394;y/P&#x2264;0.25, where &#x394;y is a protruding amount of the suction surface from the inner wall surface of the first side wall portion to the circumferential direction, and P is an arrangement pitch of the first-stage stator vanes in the circumferential direction.

Gas turbine including first-stage stator vanes

In a combustion cylinder, an outer-side region of a cooling part on an outer side with regard to a reference line orthogonal to a radial direction and an axial direction of a gas turbine and passing through a center of a combustor basket, and an inner-side region of the cooling part on an inner side with regard to the reference line are set. A connection angle at an intersection between an extension line of an outer surface of the combustor basket along the axial direction and an inner surface of a combustor transition piece is set. First regions are set at positions near the reference line, and second regions, with a larger connection angle than the first regions, are set at positions farther from the reference line than the first regions. The second regions are set to have a higher flow rate of a cooling medium than the first regions.

Combustion cylinder, gas turbine combustor, and gas turbine

A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.

Gas turbine combustor

A cylinder of a combustor includes a cylinder body inside of which combustion gas flows, a jacket plate that covers the cylinder body from the outside and forms a fluid space into which high-pressure fluid flows between an inner peripheral surface of the jacket plate and an outer peripheral surface of the cylinder body, and a rib that connects the cylinder body and the jacket plate. The rib is connected to the cylinder body by a cylinder side end portion on the cylinder body side in a radial direction with respect to an axis of the cylinder body being welded from both sides in an axial direction of the axis. The rib is connected to the jacket plate by a jacket side end portion on the jacket plate side in the radial direction being welded from both sides in the axial direction.

Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel

A gas turbine combustor is disposed in a casing interior space of a gas turbine. A combustor basket of the combustor is formed into a cylindrical shape by abutting ends of a curved panel member and welding the ends together along a welding line. A communication tube is provided for communication between an interior space of the combustor basket and an interior space of a combustor basket of an adjacent combustor. The position of the welding line of the combustor basket coincides with a connection position for connecting the communication tube to the combustor basket. A cooling air hole is disposed in the communication tube or in the combustor basket in the vicinity of the communication tube to introduce cooling air from the casing interior spaceto the interior of the combustor basket.

Growing community of inventors

Tokyo, Japan

Kentaro Tokuyama