Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Sosuke Nakamura

Yoshikazu Matsumura

Taiki Kinoshita

Shinji Akamatsu

Keijiro Saito

Takashi Sonoda

Satoshi Takiguchi

Kei Inoue

Satoshi Tanimura

Kenta Taniguchi

Akihiko Saito

Keisuke Matsuyama

Makoto Kishi

Katsunori Tanaka

Masahiro Watanabe

Satoshi Hada

Koichi Nishida

Kenichi Arase

Kiyoshi Fujimoto

Keisuke Yamamoto

Yusuke Takahashi

Kenji Miyamoto

Hiroki Shibata

Shinichi Yoshioka

Eisaku Ito

Tatsuo Ishiguro

Norihiko Motoyama

Hikaru Katano

Shinsuke Nakamura

Ryuji Takenaka

Mitsuhiro Nakao

Masaki Ono

Tetsu Konishi

Tsuyoshi Kitamura

Hiroyuki Yamasaki

Kenji Sato

Kotaro Miyauchi

Satoshi Mizukami

Yasuro Sakamoto

Koichi Akagi

Fuminori Fujii

Atsushi Yuasa

Tomo Kawakami

Takanori Ito

Mitsunori Isono

Shinichi Fukuba

Masaki Mitani

Yoshinori Wakita

Mitsuo Hasegawa

Kenichi Hashimoto

Koji Maeta

Shuhei Kajimura

Kota Yoshino

Tei Yamato

Sumiu Uchida

Eiki Anzawa

Masayuki Mawatari

Rosic Budmir

Akito Kira

Taku Egawa

Taiji Suizu

Kenichi Gotoh

Shiro Maeno

This assembly comprises a wall body in which is formed a through-hole passing through in a thickness direction, and a component fixed to one surface of the wall body so as to cover the through-hole, a welded part welded so as to fix the component to the one surface being accommodated within the through-hole.

Assembly, method for manufacturing assembly, burner, and method for manufacturing burner

A gas turbine combustor according to at least one embodiment, includes: a less combustible fuel flow control part for controlling, independently of each other, amounts of less combustible fuel supplied to a first fuel injector and a second fuel injector; a highly combustible fuel flow control part for controlling, independently of each other, amounts of highly combustible fuel having a higher combustion speed than the less combustible fuel and supplied to the first fuel injector and the second fuel injector; and a controller configured to control the less combustible fuel flow control part and the highly combustible fuel flow control part such that a relative ratio of a first ratio of the highly combustible fuel to whole of first fuel injected by the first fuel injector and a second ratio of the highly combustible fuel to whole of second fuel injected by the second fuel injector changes according to an operating condition of a gas turbine.

Gas turbine combustor with less combustable fuel and highly combustible fuel ratio control

A high-temperature part of the present disclosure includes: a high-temperature part body which includes a base and a coating layer formed on a part of a surface of the base; and a protective layer which is formed on at least a part of a surface of the coating layer. The protective layer is formed of a material which is allowed to disappear from a surface of the coating layer under an operation environment of a gas turbine.

High-temperature part and gas turbine including the same

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 state determining device determines a state of a gas turbine connected to an electric generator. The gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas.

State determining device, operation controlling device, gas turbine, and state determining method

An IGV opening command value is corrected to calculate an actual opening equivalent value that indicates an approximate value of an actual opening. A temperature estimation value, for a case where a mixture of fuel and in-flowing air is combusted, is calculated using the actual opening equivalent value, atmospheric conditions, and an output from a gas turbine. A fuel distribution command value that indicates distribution of fuel output from a plurality of fuel supply systems is calculated on the basis of the temperature estimation value. The fuel distribution command value and a fuel control signal command value that indicates the total flow rate of fuel to be output to the plurality of fuel supply systems are acquired, and respective valve openings of fuel flow rate regulating valves of the fuel supply systems are calculated on the basis of the fuel distribution command value and the fuel control signal command value.

Fuel control device and control method for a combustor of a gas turbine

A combustor includes: a pilot burner; a plurality of main burners, each of which is provided radially and outwardly along a circumferential direction about the pilot burner, and including a main nozzle disposed in a main burner cylinder; and an extension tube provided to extend toward a downstream side from the main burner cylinder of each of the main burners. The extension tube has a circular inlet communicating with the main burner cylinder, and an outlet at the downstream side comprising two radial edges parallel to the radial direction and two circumferential edges formed along the circumferential direction so as to connect both ends of the radial edges. The combustor further includes an air passage formed outside of the main burner cylinder; and an inner communication hole (formed at the side of the inlet of the extension tube and at a position corresponding to the radially and inwardly circumferential edge for allowing communication between the air passage and the inside of the extension tube.

Combustor and gas turbine

A combustor according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction.

Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.

Gas turbine combustor

A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.

Fuel control method and fuel control apparatus for gas turbine and gas turbine

In a communicating structure between combustors that generates combustion gas inside pipe pieces and a turbine portion that generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of turbine stator vanes and turbine rotor blades, at least some of the first-stage turbine stator vanes closest to the combustor among the turbine stator vanes are disposed downstream of sidewalls of one pipe piece and another pipe piece that are adjacent to each other, and the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the sidewalls of the pipe pieces to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the one pipe piece and an internal surface of the sidewall of the other pipe piece.

Communicating structure between adjacent combustors and turbine portion and gas turbine

A combustor includes a combustor external cylinder, a tubular combustor basket installed in the combustor external cylinder, a compressed air channel defined between the combustor external cylinder and the combustor basket, and a plurality of fuel nozzles installed in the combustor basket. Compressed air flowing along the compressed air channel is approximately reversed in the flow direction at an end of the combustor basket, and is introduced into the plurality of fuel nozzles. Fuel injection pegs made up of an upstream side fuel injection peg injecting upstream side fuel and a downstream side fuel injection peg injecting downstream side fuel, are installed in the compressed air channel. Concentration fluctuation of the upstream side fuel caused by pressure fluctuation in the combustor is configured so as to reduce a peak of concentration fluctuation of the downstream side fuel at a combustion start position of the combustor.

Combustor with fuel injector pegs for reducing combustion pressure oscillations

An acoustic damper of the present invention is objected to obtain a sound absorption effect of a combustor in an extensive range of frequency band. The acoustic damper includes an acoustic pipe body attached to a combustor so as to communicate with an inside of the combustor, and the acoustic pipe body is provided with a plurality of passages whose extension lengths are different from each other inside the acoustic pipe body.

Acoustic damper, combustor and gas turbine

Growing community of inventors

Hyogo, Japan

Sosuke Nakamura