Hitachi, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Hitachi Chemical Company, Ltd.

Mitsubishi Power, Ltd.

Yoshitaka Hirata

Hirokazu Takahashi

Kazuo Takahashi

Hiroshi Inoue

Akinori Hayashi

Shouhei Yoshida

Shohei Yoshida

Tomohiro Asai

Tomoya Murota

Satoshi Dodo

Yasuhiro Akiyama

Toshifumi Sasao

Kazuyuki Itou

Keisuke Miura

Kazunori Yamamoto

Yasushi Shimada

Tatsuya Sekiguchi

Hiroyuki Kuriya

Mitsuhiro Karishuku

Kazuhisa Otsuka

Nariyoshi Kobayashi

Masanori Yamaguchi

Tomoki Uruno

Tomomi Koganezawa

Isao Takehara

Kazuki Abe

Yuusuke Kondou

Shohei Numata

Etsuo Mizushima

Yuichi Shimayama

Tatsuya Hagita

Keita Yunoki

Shota Igarashi

Ken Madarame

Kenji Miyamoto

Koichi Nishida

Satoshi Takiguchi

Hiroshi Okabe

Yasuhiro Wada

Shin Takanezawa

Susumu Nakano

Eriko Takeda

Hiromi Koizumi

Kuniyoshi Tsubouchi

Yasushi Kumashiro

Yoshitaka Terada

Hirozi Yamada

Yoshinori Matsubara

Hiroyuki Takeishi

Takeo Saitou

Keita Naito

Noboru Okuyama

Nozomi Saitou

Kanetsugu Nakamura

Takehiko Nishikawa

Naoto Fujiwara

A control method for a gas turbine combustor including an air-hole plate having a plurality of air holes formed therein, and a plurality of fuel nozzles corresponding to respective ones of the plurality of air holes. The gas turbine combustor is operable to combust a hydrogen fuel and a fuel other than the hydrogen fuel. The air holes include: first air holes having, among passageways from an entry end to an exit end, an inclined passageway extending in a direction inclined with respect to the central axis of the air-hole plate in a region including at least the exit end; and second air holes extending in parallel to the central axis. The fuel nozzles include first fuel nozzles corresponding to respective first air holes, and second fuel nozzles corresponding to respective second air holes. During hydrogen fuel firing, the hydrogen fuel is not supplied to the first fuel nozzles.

Control method for gas turbine combustor and control device for gas turbine combustor

A gas turbine combustor includes a vane, a plurality of supports, and a pressure dynamics damping hole. The vane is disposed at the outer circumferential side of the combustion liner. The plurality of supports are disposed at an inner side of the combustion casing for fixing the vane. The pressure dynamics damping hole is formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.

Gas turbine combuster

This gas turbine equipment comprises a gas turbine and a control device. A combustor of the gas turbine uses ammonia as fuel, and uses the RQL method. A compressor of the gas turbine includes an intake adjustor that adjusts an intake rate which is the flow rate of air that flows into a compressor casing. When the concentration of NOx in exhaust gas reaches or exceeds a predetermined value, the control device controls the operation of the intake adjustor so that the intake rate decreases.

Gas turbine equipment with compressor airflow control responsive to NOx concentration and control method thereof

Provided is a burner of double tube structure including an outer tube and an inner tube. The inner tube includes a tip-side support portion fixed on the outer tube, a base-side support portion fixed on the outer tube, a main body portion supported by the tip-side support portion, bellows interposed between the main body portion and the base-side support portion, and a bulkhead member attached at a position between the tip-side support portion and the base-side support portion. Between an outer peripheral surface of the bulkhead member and an inner peripheral surface of the outer tube, a second gap smaller than a first gap between an outermost peripheral surface of the bellows and the inner peripheral surface of the outer tube is interposed.

Burner and combustor

A hydrogen content fuel can be stably ignited using a gaseous fuel that does not contain hydrogen and dispersibility of the hydrogen content fuel is enhanced. A gas turbine combustor including a burner including: a startup fuel pipe in which a startup fuel circulates; a first main fuel pipe in which a main fuel circulates, a second main fuel pipe in which the main fuel circulates; a fuel mixer to which the startup fuel pipe and the first main fuel pipe are connected; an inner fuel nozzle to which the fuel mixer is connected; a plurality of outer fuel nozzles to which the second main fuel pipe is connected; a startup fuel control valve provided in the startup fuel pipe; a first fuel control valve provided in the first main fuel pipe; and a second fuel control valve provided in the second main fuel pipe.

Gas turbine combustor and its operating method

A transition piece includes a first flow passage group formed by arranging a plurality of intra-wall flow passages, a second flow passage group, and a plurality of dilution holes that penetrate a plate, and establish communication between a compressed air main flow passage and a combustion gas flow passage, each intra-wall flow passage of the first flow passage group and the second flow passage group having an inlet facing the compressed air main flow passage at an end portion on a side near the gas turbine, and having an outlet facing the combustion gas flow passage at an end portion on a side near the combustor liner, a dilution hole being located nearer to the inlet of an intra-wall flow passage of the second flow passage group than to the outlet of the intra-wall flow passage of the second flow passage group.

Transition piece, combustor, and gas turbine engine

A gas turbine combustor includes multiple aft frames each having a floating seal that seals a gap between an aft frame and a gas turbine in inner and outer peripheries of the aft frame, and a side seal that seals a gap between the aft frames adjacent to each other in a circumferential direction, and a corner seal that is placed in a gap portion provided between corner portions of the aft frames adjacent to each other in the circumferential direction, seals air leaking from at least the gap portion into the gas turbine side, and is independent of the floating seal and the side seal.

Gas turbine combustor

Adhesion of particulate matters to the burner accompanying combustion in a lean-combustion gas turbine combustor is suppressed, and the structural reliability is improved. In a gas turbine combustor including: a tubular liner that forms a combustion chamber; and a burner including an air hole plate that is arranged at an inlet of the liner and includes a plurality of air holes for guiding compressed air to the combustion chamber, and a plurality of fuel nozzles that are arranged on a side opposite to the combustion chamber with the air hole plate being sandwiched therebetween, the plurality of fuel nozzles each injecting a fuel toward a corresponding air hole, the air holes and the fuel nozzles forming a plurality of concentric annular lines, a plurality of small holes having opening diameters smaller than those of the air holes are provided through the air hole plate such that the plurality of small holes are positioned in an inner area of an innermost annular line of the air holes.

A combustor includes: a first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.

Combustor, gas turbine

The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.

Gas turbine combustor and method of operating the same

The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip. The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.

A combustor is capable of ignition and flame propagation at low fuel concentrations for gas or liquid fuel. Combustors are disposed annularly along an outer peripheral portion of a casing of a turbine. A combustion chamber burns fuel and air to generate a combustion gas. A diffusion burner is disposed upstream of the combustion chamber; and a plurality of premix burners are disposed around the diffusion burner. Cross fire tubes provide communication between combustion chambers of combustors adjacent to each other. A cross fire tube connected to a combustor adjacent to a first side in the circumferential direction of the casing is disposed so as to have a central axis passing over a premix burner as viewed from the combustion chamber and another cross fire tube connected to the combustor adjacent to a second side is disposed so as to have a central axis passing between two premix burners.

A combustor has at least one premixing burner for premixing fuel with air and jetting the mixed gas into a chamber for combustion. A cylinder attached to an outer circumferential portion of an end face of the burner is provided with air supply holes. An interval Ddefined between the adjacent air supply holes and an interval Ddefined between each air supply hole and the end face of the burner are each made narrower than the quenching distance in the premixed gas jetted from the premixing burner.

Gas turbine combustor with a premixing burner having a reduced metal temperature by injecting air along a burner end face

An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising: a rotating speed detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, and a fuel control unit for judging a starting situation of reduction in the rotating speed of gas turbine on the basis of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and controlling respectively a fuel flow rate for the diffusion combustion burner to be fed to the diffusion combustion burner installed in the gas turbine combustor and a fuel flow rate for the premix combustion to be fed to the premix combustion burner.

Method and apparatus for controlling gas turbine combustor

There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions. The gas turbine combustor includes: a cylindrical combustion chamber that burns combustion air and fuel to thereby produce combustion gas; an outer casing disposed concentrically on an outside of the combustion chamber; an end cover disposed at an upstream side end portion of the outer casing; an annular passage formed by an outer peripheral surface of the combustion chamber and an inner peripheral surface of the outer casing, the annular passage allowing the combustion air to flow therethrough; and a passage formed inside a combustion chamber wall between the outer peripheral surface and an inner peripheral surface of the combustion chamber, the passage having a U-shape turned sideways and having ends disposed on an upstream side in a transverse cross-sectional view, in which the passage includes a first passage that extends in parallel with an axial direction of the combustion chamber and has a supply hole on a first end side thereof, the supply hole communicating with an outside of the combustion chamber wall, and a second passage that has a second end side communicating with a second end side of the first passage and has a jet hole on a first end side thereof, the jet hole communicating with an inside of the combustion chamber wall.

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Hitachi, Japan

Yoshitaka Hirata