Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Mitsubishi Jukogyo Kabushiki Kaisha

Satoshi Tanimura

Shigemi Mandai

Shinji Akamatsu

Koichi Ishizaka

Toshihiko Saito

Keijiro Saito

Koichi Nishida

Masataka Ohta

Atsushi Yuasa

Jose Rodriguez

Toshihiko Saitoh

Kenta Kurihara

Katsunori Tanaka

Satoshi Takiguchi

Kenta Taniguchi

Keisuke Matsuyama

Sosuke Nakamura

Kei Inoue

Hideyuki Uechi

Kazufumi Ikeda

Hideki Haruta

Mitsuru Inada

Katsuyoshi Tada

Masataka Ota

Tetsuo Gora

Masakazu Nose

Yukio Tanaka

Kenji Miyamoto

Eisaku Ito

Tatsuo Ishiguro

Takashi Sonoda

Akihiko Saito

Makoto Kishi

Hidefumi Araki

Satoshi Mizukami

Shinsuke Nakamura

Ichiro Fukue

Takanori Ito

Jun Sasahara

Hiroyuki Nishida

Keijiro Saitoh

Kuniaki Aoyama

Tetsu Konishi

Masanori Yuri

Shunsuke Torii

Kotaro Miyauchi

Katsuhiko Abe

Keizo Tsukagoshi

Taiki Kinoshita

Yasuro Sakamoto

Fuminori Fujii

Hiroaki Kishida

Yuichi Ichikawa

Hikaru Kurosaki

Mitsuhiro Karishuku

Atsushi Moriwaki

Yoshitaka Terada

Yutaka Kawata

Yoshifumi Masuda

Yoshichika Sato

Jun Kubota

Yoshiaki Yamaguchi

Tatsuya Hagita

Takaaki Hase

Masaki Mitani

Hiroshi Makigano

Norihiko Nagai

Keita Naito

Hitoshi Kawabata

Kouichi Nishida

Masaya Kato

Nobuo Sato

Teruya Tachibana

Tadashi Kamiya

Tomohisa Takasaki

Nobuo Satoh

Shohei Domen

H Lindsay Morton

Robert D Zangara

A raw material fluid treatment plant provided with a raw material reaction apparatus for reacting a raw material fluid to form a reaction gas. The raw material reaction apparatus includes preheaters and a reactor. The preheaters are heat exchangers that perform heat exchange between a second heat transfer medium and the raw material fluid to heat the raw material fluid. The reactor is a heat exchanger that performs heat exchange between a first heat transfer medium differing from the second heat transfer medium and the raw material fluid having been heated by the preheaters to heat and react the raw material fluid.

Raw material fluid treatment plant and raw material fluid treatment method

A gas turbine including a fuel gas supply system to supply fuel gas via a fuel piping to a gas turbine combustor, a pressure control valve installed halfway along the fuel piping, a flow control valve installed in the fuel piping at downstream of the pressure control valve, and a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P1 at upstream of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P1.

Gas turbine and method for adjusting flow rate of fuel supplied thereto

An ammonia decomposition facility includes a heating medium line configured to flow a heating medium heated by heat generated by a gas turbine, an ammonia supply line configured to flow ammonia, an ammonia decomposition device, and an ammonia removal device. The ammonia decomposition device is configured to use heat of the heating medium from the heating medium line, thermally decompose ammonia from the ammonia supply line, and generate a decomposition gas containing hydrogen, nitrogen, and residual ammonia. The ammonia removal device is configured to remove the residual ammonia contained in the decomposition gas from the ammonia decomposition device.

Ammonia decomposition facility, gas turbine plant equipped with same, and ammonia decomposition method

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 includes: a casing having an air chamber filled with air; at least one mixing passage forming member forming at least one mixing passage which is connected at an inlet side to the air chamber and at an outlet side to a combustion chamber and having an inlet at the inlet side of the at least one mixing passage so as to communicate with the air chamber; and at least one fuel nozzle disposed inside the air chamber and having a fuel injection hole, positioned upstream of the inlet of the at least one mixing passage forming member, for injecting fuel downstream.

Combustor and gas turbine including the same

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

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

A gas turbine plant is provided with a gas turbine, a heating device, a decomposition gas line, and a decomposition gas compressor. The heating device heats ammonia and thermally decomposes the ammonia to convert the ammonia into decomposition gas including hydrogen gas and nitrogen gas. The decomposition gas line sends the decomposition gas PG from the heating device to the gas turbine. The decomposition gas compressor increases the pressure of the decomposition gas to a pressure equal to or higher than a feed pressure at which the decomposition gas is allowed to be fed to the gas turbine.

Gas turbine plant having thermal decomposition of ammonia and pressurization of the decomposed gas and method thereof

A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.

Gas turbine combustor transition piece including inclined surface at downstream end portions for reducing pressure fluctuations

A fuel injector including a fuel supply tube (), a plurality of premix tubes (), a support plate () which supports the fuel supply tube and the plurality of premix tubes, a substrate which supports downstream end portions of the plurality of premix tubes, an outer wall which is cylindrical, which forms a plenum (P) inside, a partition plate which partitions the plenum (P) into a fuel plenum (PF) and a cooling air plenum (PA), a baffle which partitions the cooling air plenum (PA) into an upstream cooling air plenum (PA) and a downstream cooling air plenum (PA) and has a plurality of cooling holes formed therein, and a cooling air supply tube configured to supply cooling air to the upstream cooling air plenum (PA), in which the end portion on the downstream side of the fuel supply tube opens in the fuel plenum (PF), and a fuel introduction hole.

Fuel injector and gas turbine

A cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.

Cylinder for combustor, combustor, and gas turbine

Provided is a combustor that is made compact and achieves NOx reduction. In the combustor () including a pilot nozzle () disposed along the central axis of the combustor () and performing diffusion combustion, a plurality of main nozzles () disposed on the outer peripheral side of the pilot nozzle () at intervals in the circumferential direction and performing premixing combustion, a single inner cylinder () surrounding the pilot nozzle () and the main nozzles (), and an outer cylinder approximately coaxially surrounding the outer side of the inner cylinder () to form a compressed air passage () between the inner peripheral surface thereof and the outer peripheral surface of the inner cylinder and turning the flow direction of compressed air flowing in the compressed air passage () in approximately the opposite direction at the end of the inner cylinder () to introduce the compressed air into the pilot nozzle (), the compressed air passage () is provided with a flow rate controller that makes the flow rate on the combustor () inner peripheral side of the passage larger than that on the outer peripheral side. An example as the flow rate controller is a baffle plateprovided with holes

Combustor

In a damping device according to the present invention, a damping deviceis mounted on a bypass pipethat supplies an amount of high-pressure air to a combustor transition piece. The damping deviceincludes a fluid introducing unitthat forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe, a plurality of acoustic boxesandthat forms resonance spaces Da and Db with the base portions connected to the fluid introducing unitand the end portions extending along the outer peripheral portion of the bypass pipein the circumferential direction, and partition platesandthat form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Damping device and 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

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Hyogo, Japan

Satoshi Tanimura