Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Kenta Taniguchi

Shinji Akamatsu

Satoshi Takiguchi

Taiki Kinoshita

Kenji Sato

Kentaro Tokuyama

Kenji Miyamoto

Keijiro Saito

Kei Inoue

Naoki Abe

Yoshikazu Matsumura

Satoshi Tanimura

Keisuke Miura

Kiyoshi Fujimoto

Sosuke Nakamura

Tomo Kawakami

Katsuyoshi Tada

Hiroyuki Sakaki

Shinichi Fukuba

Shingo Sato

Masaki Ono

Keisuke Matsuyama

Shin Kato

Kuniomi Hirano

Yusuke Tanaka

Shinya Hashimoto

Hiroyuki Yamasaki

Kotaro Miyauchi

Takahiro Kondo

Satoshi Mizukami

Tomohiro Asai

Norihiko Motoyama

Naoki Tsunoda

Takashi Hiyama

Yuichi Ichikawa

Yoshitaka Terada

Hikaru Katano

Kenichi Hashimoto

Yoshinori Wakita

Shuhei Kajimura

Toshinobu Ohara

Katsuyoshi Omae

Yugo Tokunaga

Takashi Onozuka

Shohei Domen

Yoshiro Nakamura

Tatsuya Kowari

Ryota Fukuoka

Taku Egawa

Kazuhiro Tominaga

Zhi Zhang

A combustor of the present disclosure includes a combustor plate configured to have a downstream end face perpendicular to a combustor axis; a nozzle segment configured such that a plurality of first nozzles that inject a premixed gas of air and fuel from a side of the downstream end face are collectively disposed; and a plurality of second nozzles configured to inject the fuel from the downstream end face. A plurality of the nozzles segments are provided at intervals in a direction perpendicular to the combustor axis. Each of the second nozzles injects the fuel from a dividing region between the nozzle segments on the downstream end face.

Combustor and gas turbine

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 burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each of the at least one fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each of the at least one fuel nozzle includes at least one fuel injection hole formed on a side surface of the protruding portion. A top surface of the protruding portion includes a convex curved surface.

Burner assembly, gas turbine combustor, and gas turbine

A tail pipe () comprises: a pipe (); an acoustic attenuator () that forms an acoustic space (Ss) on the outer peripheral side of the pipe (); and a cooling air jacket () that forms a cooling air space (Sa) isolated from the outer space (So), which is the space on the outer peripheral side of the pipe (). The pipe () has: a first air flow path () that is formed between the outer peripheral surface () and the inner peripheral surface (); and an acoustic hole () that penetrates from the acoustic space (Ss) to a combustion space (Sc), which is a space on the inner peripheral side of the pipe (). The first air flow path () has: an inlet () that faces into the cooling air space (Sa) and guides the air in the cooling air space (Sa) into the first air flow path (); and an outlet () that faces into the acoustic space (Ss) and guides the air passing through the first air flow path () into the acoustic space (Ss).

Transition piece, combustor, gas turbine, and gas turbine equipment

A combustor includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which an air hole passing through the upstream side end face and the downstream side end face is formed in the tube plate; and a fuel injector that injects fuel into air passing through the air hole. The air hole has: a bent channel that curves toward a direction orthogonal to the combustor axis toward the downstream side; and an inclined channel that is connected to the downstream side of the bent channel so as to be continuous therewith, and that extends inclining with respect to the combustor axis and opens to the downstream side end face. A fuel injection position at which the fuel injector injects fuel is located on the downstream side of the upstream end of the bent channel.

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

The upstream-side wall portionincludes, in the circumferential direction thereof, a first regionwhere air inletsare formed at a lower density, and a second regionwhich is disposed at a position offset from the first regionin the circumferential direction, and in which the air inletsare formed at a higher density than in the first region

Combustor and gas turbine including the combustor

A combustor for a gas turbine includes: a flange portion to be mounted to a casing; an extension portion having an annular shape and extending from the flange portion along an axial direction of the combustor; a pipe portion having a first end connected to the flange portion and a second end connected to an outer peripheral surface of the extension portion, the pipe portion extending from the first end to the second end at an outer side of the extension portion in a radial direction; and at least one fuel nozzle configured to receive supply of a fuel via the pipe portion and a passage disposed inside the extension portion.

Combustor for gas turbine and gas turbine having the same

A gas turbine combustor is equipped with a nozzle in which an air ejection passage extending along an axis and having an open distal end, and a fuel supply passage extending along the axis and having an open distal end are formed; swirling vanes provided around the nozzle so as to be twisted around the axis of the nozzle; an inner cylinder surrounding an outer periphery of the nozzle and the swirling vanes, and in which compressed air flows through an inside of the inner cylinder toward a downstream side; an outer cylinder which defines an inversion flow path, which inverts the compressed air on an outer periphery of the inner cylinder and introduces the compressed air to the inside of the inner cylinder, between the inner and outer cylinders; and an air introduction pipe having one end connected to a space on an upstream side of the compressed air from the inversion flow path, and the other end connected to the air ejection passage.

Gas turbine combustor and gas turbine

A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which extends along the axis and through which first fuel is configured to flow, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and is configured to eject the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air is configured to flow, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured eject the purge air from the center of the distal end.

Combustor nozzle, combustor, and gas turbine

The present invention is a downstream plate which is provided on a downstream side of an upstream plate includes an air inlet into which cooling air is introduced from a cooling air introduction pipe and a cooling flow path which extends in a direction along a surface of the downstream plate from the air inlet so as to avoid a premix tube and through which cooling air flows.

Fuel injector, combustor, and gas turbine

An acoustic device includes: a perforated plate that has a plurality of holes penetrating in a plate thickness direction of the perforated plate and in which a main flow is to flow on a first side of the perforated plate in the plate thickness direction; and a housing that is on a second side of the perforated plate in the plate thickness direction and partitions a space between the housing and the perforated plate, wherein a part of each of the plurality of holes on the first side in the thickness direction is inclined to at least one of the first side and a second side of a flow direction of the main flow.

Acoustic device and gas turbine

Growing community of inventors

Yokohama, Japan

Kenta Taniguchi