Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Shinji Akamatsu

Satoshi Takiguchi

Koichi Nishida

Keijiro Saito

Shigemi Mandai

Satoshi Tanimura

Kotaro Miyauchi

Kenta Taniguchi

Naoki Abe

Keisuke Matsuyama

Hideki Haruta

Katsunori Tanaka

Kenji Sato

Sosuke Nakamura

Masataka Ohta

Masataka Ota

Toshihiko Saito

Kei Inoue

Kenji Miyamoto

Taiki Kinoshita

Naoki Tsunoda

Yusuke Tanaka

Takashi Sonoda

Akihiko Saito

Makoto Kishi

Satoshi Mizukami

Shinsuke Nakamura

Koichi Akagi

Kentaro Tokuyama

Hiroaki Kishida

Kazufumi Ikeda

Rintaro Chikami

Yoshikazu Matsumura

Mitsuhiro Nakao

Tomo Kawakami

Mitsuru Inada

Yoshichika Sato

Takanori Ito

Shinichi Fukuba

Shuhei Kajimura

Kazuya Kobayashi

Takayoshi Takashima

Yuichiro Kimura

Yoji Kochi

Teruya Tachibana

Hiroki Shibata

Kuniaki Aoyama

Kiyoshi Fujimoto

Norihiko Motoyama

Ichiro Fukue

Wataru Akizuki

Atsushi Moriwaki

Katsuyoshi Tada

Masakazu Nose

Tetsuo Gora

Masaki Mitani

Hikaru Katano

Toshihiko Saitoh

Yoshinori Wakita

Yoshikuni Kasai

Norihiko Nagai

Kota Yoshino

Keijiro Saitoh

Eiji Takami

Issei Tamura

Masahiro Kamogawa

Tomohisa Takasaki

Taehwan Kim

Taku Egawa

Hisanari Nakajima

Jyunji Hashimura

A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

Fuel injector, combustor including the fuel injector, and gas turbine including the combustor

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 gas turbine combustor according to at least one embodiment is a gas turbine combustor that includes: a tubular member; a plurality of premixing tubes circumferentially arranged on an inner side of the tubular member, each of the plurality of premixing tubes forming an outlet portion of a premixing passage; and a base plate for supporting the plurality of premixing tubes. The base plate has: a plurality of through holes disposed corresponding to the plurality of premixing tubes, respectively, and allowing the premixing passage to pass through the base plate; and a plurality of oblique holes extending obliquely with respect to an axial direction of the gas turbine combustor in a region different from a region where the through holes are disposed.

Gas turbine combustor and gas turbine

A combustor component of a combustor for combusting fuel to produce a combustion gas includes a combustion cylinder forming a passage for the combustion gas, a first acoustic device which internally includes a first cavity communicating with the passage via a first through hole formed in the combustion cylinder, a second acoustic device which is located on a radially outer side of the first acoustic device so as to cover the first acoustic device, and internally includes a second cavity communicating with the passage via a second through hole formed in the combustion cylinder, and a first communication passage causing the first cavity and an outer space of the combustion cylinder to communicate with each other without via the first through hole and the second cavity.

Combustor component, combustor including the combustor component, and gas turbine including the combustor

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

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

A gas turbine combustor provided with: a plurality of swirler tubes that are disposed inside a combustor basket and impart a swirl to a premixed gas, the premixed gas being obtained by premixing a fuel and air for combustion; and an outer ring that is disposed between the plurality of swirler tubes and the combustor basket with a gap provided between the outer ring and the combustor basket, and generates film-shaped air inside a combustor transition piece connected to the combustor basket via injection through the gap into the combustor transition piece, and at a downstream end of the outer ring, the outer ring includes a tapered surface formed such that the outer ring gradually decreases in thickness from an upstream side toward a downstream side.

Gas turbine combustor

A combustor provided with: a nozzle having formed therein an air jet section that causes air to be jetted from a nozzle section; a cylindrical part covering the nozzle from the outer peripheral side thereof and forming an air flow path between the cylindrical part and the nozzle; and a pressure loss section provided to the air flow path. The pressure loss section causes a loss of pressure in the air that flows through the air flow path. The nozzle is provided with: at least one air inlet section that takes in air from an outer peripheral surface that is an upstream side from the pressure loss section; and a flow path-forming section forming a discharge air flow path that guides air that is taken in from the at least one air inlet section to the air jet section.

Nozzle, burner, combustor, gas turbine, and gas turbine system

A burner assembly for a combustor includes: a plurality of first nozzles arranged in a circumferential direction of the combustor; a plurality of first burner cylinders accommodating the respective first nozzles; and a middle-flow-passage forming portion which is connected to a downstream end of the plurality of first burner cylinders and which forms a middle flow passage through which a combustion chamber of the combustor is in communication with an interior space of each of the plurality of first burner cylinders. The middle-flow-passage forming portion includes an inner peripheral wall disposed on a radially inner side of the combustor and formed such that a distance from a center axis of the combustor to the inner peripheral wall is uneven with respect to the circumferential direction.

Burner assembly, combustor, and gas turbine

There is provided a combustor including a nozzle main body () that includes a shaft body () which extends along an axis and has, inside the shaft body (), a purge air flow path (), which extends along the axis to a tip portion of the shaft body () and into which compressed air is introduced, and an air spraying hole (), which is formed in the tip portion of the shaft body () and connects the purge air flow path () to an outer surface of the shaft body (), a swirling blade (), which overhangs from an outer circumferential surface of the shaft body () in a diameter direction of the axis and swirls a fluid flowing to a downstream side of an axial direction around the axis, and a fuel spraying hole (), and a sealing member () that seals the air spraying hole () and is formed of a metal having a melting point lower than a melting point of a metal forming the nozzle main body ().

Combustor and gas turbine

A combustor includes a nozzle, a burner cylinder surrounding the outer circumference of the nozzle, and an outside flow path cylinder surrounding the outer circumference of a downstream end portion of the burner cylinder. A purge air flow path through which air flows is formed between the inner circumferential side of the outside flow path cylinder and the outer circumferential side of the burner cylinder. A tapered surface is formed in the downstream end portion of the burner cylinder such that the plate thickness of a burner cylinder-forming plate that forms the burner cylinder gradually thins toward the downstream side.

Combustor and gas turbine comprising same

A combustor () includes a plurality of first burners extending along an axis (P) and arranged at intervals in the circumferential direction, a base plate () having support openings configured to support the plurality of first burners and a plurality of through-holes () through which base plate air flows toward a downstream side, a plurality of extension pipes supported by the base plate () to correspond to the first burners and configured to guide a pre-mixed gas ejected from the first burners toward the downstream side, and a base plate air guide section () configured to change a direction of at least some of the base plate air ejected from the through-holes () at a downstream side of the base plate ().

Gas turbine combustor base plate configuration

A combustor includes: a first nozzle which extends along an axis and injects fuel toward a downstream side; a flame stabilizer which covers a downstream-side end portion of the first nozzle from an outer periphery side; and a plurality of second nozzles arranged at intervals in a circumferential direction around the axis on the outer periphery side of the flame stabilizer. The flame stabilizer has a cone portion expanding in diameter toward the downstream side from the upstream side, and a flange portion extending radially outward from a downstream-side end edge of the cone portion, and a penetrating portion which penetrates at least the flange portion in a direction of the axis is formed in the flame stabilizer.

Gas turbine combustor flame holder

To provide a gas turbine combustor that can suppress a generation amount of NOx and maintain a flame holding property, while suppressing burn damage around a pilot nozzle including the pilot nozzle. A gas turbine combustor includes a pilot nozzle that can inject fuel F and cooling air A for cooling a nozzle tip, a flow regulating valve that can adjust a flow rate of cooling air to be supplied to the pilot nozzle, a detection sensor that detects a combustion state of fuel, and a control device that controls the flow regulating valve based on a detection result of the detection sensor.

Gas turbine combustor, gas turbine, control device, and control method

A combustor including a transition piece that defines a flow channel therein; a combustor basket inserted in the transition piece from an upstream side of the flow channel that sends a combustion gas through the flow channel and defines a gap through which a compressed air is sent with an inner peripheral surface of the transition piece; wherein the combustor basket includes a notch portion recessed from an end of the combustor basket on a downstream side toward the upstream side, and a purge air introduction hole through which the compressed air in the gap is introduced into the notch portion.

Growing community of inventors

Yokohama, Japan

Shinji Akamatsu