Hitachi, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Satoshi Dodo

Shohei Yoshida

Hirokazu Takahashi

Hiroshi Inoue

Keisuke Miura

Yoshitaka Hirata

Kuniyoshi Tsubouchi

Mitsuhiro Karishuku

Tomomi Koganezawa

Hiromi Koizumi

Tomohiro Asai

Akinori Hayashi

Hiroshi Arita

Kazuhito Koyama

Susumu Nakano

Kazuki Abe

Manabu Yagi

Yasuhiro Akiyama

Takeo Saito

Yasuaki Akatsu

Norio Yasugahira

Shigeo Hatamiya

Makoto Hemmi

Tomoaki Inoue

Satoshi Kumagai

Tadaharu Kishibe

Yoshihide Wadayama

Keita Naito

Itsurou Sawada

Noboru Okuyama

Kanetsugu Nakamura

Nobuo Yagi

Koizumi Hiromi

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

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

[Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.

Fuel nozzle of gas turbine combustor and manufacturing method thereof, and gas turbine combustor

To achieve a reduction in waste heat loss of a fuel with improved efficiency in arrangement of a plurality of cavities, or manifold spaces. A multi-stage combustor includes a combustor liner configured to define a combustion chamber therein, a plurality of fuel nozzles configured to inject a fuel, and a manifold configured to distribute the fuel to the plurality of fuel nozzles. The manifold is disposed on a central axis of the combustor liner in a central axis extending direction. The manifold includes a casing and a plurality of partitions inserted in the casing so as to be arranged in a central axis direction of the combustor liner to define a plurality of cavities divided by the partitions. The plurality of cavities are layered in the central axis direction of the combustor liner inside of the casing, and are connected to the corresponding fuel nozzles.

Combustor and 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.

Gas turbine combustor

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

A combustor is provided that can ensure combustion stability even when operated on low BTU gas without needing any equipment for preventing back-flow of fuel gas during operation on pilot fuel. The combustor includes a first perforated plate disposed upstream of a combustion chamber, the first plate having a plurality of nozzle holes and air holes; a second perforated plate disposed on the upstream side of the first plate; and a plurality of gas nozzles each of which is inserted into corresponding nozzle holes. The gas nozzle has a leading end located inside the corresponding one of the nozzle holes. Each of the gas nozzles includes a jet hole portion having a diameter smaller than that of a gas jet hole of the gas nozzle; and a passage portion designed to form an air passage on the outer circumference of the leading end portion of the gas nozzle.

Combustor, burner, and gas turbine

A gas turbine combustor stably burns low-BTU gases, such as blast furnace gases, that are heavily laden with CO. The gas turbine combustor includes a double-swirling burner with an inner swirler and an outer swirler, the burner having a configuration with gas fuel injection holes and air injection holes arranged at alternate positions in the inner swirler and with gas injection holes arranged in the outer swirler. In addition, fuel injection holes for enhancing flame stability are provided at positions radially inward of the inner swirler. An inner flame by the inner swirler and an outer flame by the outer swirler interact with each other to stably burn the low-BTU gas. In the inner swirler, the gas injection holes and air injection holes arranged at alternate positions contributes to raising a temperature of the inner flame to a level required for flame stabilization.

Gas turbine combustor and method for operating same

This invention is directed to supply a combustor having a structure that reduces NOx emissions while maintaining combustion stability. The combustor has a chamber into which fuel and air are supplied. An air hole plate having a plurality of air holes upstream of the chamber is also disclosed, and fuel nozzles supplying fuel to the air holes of the air hole plate are further disclosed. In the combustor, a center of a chamber-side of the air hole plate is closer to the chamber than exits of outermost peripheral air holes.

Combustor and operating method thereof

A combustor of the prior art that defines the outlet position and direction of an air hole and suppresses adhesion of flame to an air hole outlet can reduce a discharge amount of NOx by increasing a distance over which fuel and air are mixed with each other. However, such a combustor is not sufficiently discussed for measures to suppress the occurrence of combustion oscillation resulting from the variation of a flame surface. A combustoraccording to the present invention includes a combustion chamberto which fuel and air are supplied; air holesadapted to supply air to the combustion chamber; fuel nozzlesadapted to supply gaseous fuel to the air holes; and orificesadapted to allow the gaseous fuel supplied to the air holesto cause a pressure drop.

Gas turbine gaseous fuel injection system

A combustor includes a fueling nozzle that jets a fuel towards a combustion chamber located downstream and a flat-plate-shaped air blowhole plate that faces the upstream side of the combustion chamber and that is disposed between the fueling nozzle and the combustion chamber. The air blowhole plate has a plurality of air blowholes arranged at equal intervals in a circumferential direction relative to the center of the air blowhole plate, in order to jet a flow of fuel and a flow of air that is formed at the outer circumferential side of the fuel flow toward the combustion chamber.

Combustor having modified spacing of air blowholes in an air blowhole plate

An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen. In the secondary combustion zone, air for lean combustion is supplied into the combustion chamber so that unburned part of fuel is combusted under a fuel lean condition.

Low NOx combustor for hydrogen-containing fuel and its operation

An object of this invention is to suppress adhesion of a flame to periphery of air hole outlets arranged on an air hole plate. A combustor includes a fuel nozzle for jetting out a fuel into a combustion chamber formed at a downstream side; an air hole plate of a flat-plate shape disposed between the fuel nozzle and the chamber, the air hole plate facing an upstream side of the chamber; and a plurality of air holes provided in the air hole plate, in a circumferential direction relative to a central axis of the air hole plate, such that a fuel flow and an air flow formed at an outer circumferential side of the fuel flow are blown out into the chamber from the respective air holes; wherein a clearance defined between any two circumferentially adjacent air hole inlets provided on a face of the air hole plate that is nearer to the fuel nozzle is wider than a clearance defined between any two circumferentially adjacent air hole outlets formed on a face of the air hole plate that is nearer to the chamber. According to the invention, adhesion of a flame to peripheral sections of the air hole outlets disposed on the air hole plate can be suppressed.

Combustor, method of supplying fuel to same, and method of modifying same

A combustor for a gas turbine capable of performing stable combustion even by using high temperature air, comprising a first burner () jetting fuel and air into a combustion chamber () and a second burner () causing the circulating jet of the fuel and air installed at a position corresponding to the tip part of a flame caused by the first burner ().

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Kasama, Japan

Satoshi Dodo