Canon Kabushiki Kaisha

Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Kei Inoue

Keijiro Saito

Masashi Hirose

Yasuaki Murai

Takayuki Toyoda

Shinji Akamatsu

Kenta Taniguchi

Sosuke Nakamura

Takeshi Miyazaki

Satoshi Tanimura

Masatake Tanaka

Masashi Kawamura

Kazuyuki Sato

Naoki Abe

Yutaka Tani

Yoshikazu Matsumura

Katsuyoshi Tada

Kenji Miyamoto

Taichi Shintou

Satoshi Takiguchi

Ryuji Murayama

Yuki Hasegawa

Yuichi Ichikawa

Soichiro Kawakami

Katsunori Tanaka

Koichi Nishida

Eisaku Ito

Akio Maruyama

Yukio Nagase

Atsushi Nakamoto

Masayoshi Kato

Waka Hasegawa

Kuniaki Aoyama

Minako Kawabe

Manami Haraguchi

Makoto Fukatsu

Kotaro Miyauchi

Kenji Nishiguchi

Toshiyuki Osada

Takashi Hiyama

Hideki Haruta

Atsushi Yuasa

Tomo Kawakami

Jun Shirakawa

Kaoru Takahashi

Masashi Tagawa

Masahiro Suenaga

Mitsunori Isono

Kazuta Kobayashi

Hikaru Katano

Naonori Nagai

Keita Yunoki

Shuhei Kajimura

Ryosuke Nagao

Otome Mori

Manabu Maeda

Eiji Takami

Shohei Domen

External additive particles including a polymer containing a sulfur atom and a nitrogen atom, wherein the polymer includes a vinyl polymer moiety and a siloxane moiety, relative to a total number of carbon atoms, oxygen atoms, and silicon atoms constituting the external additive particles, a ratio of a number of the silicon atoms constituting the external additive particles is 4.0% or more and 25.0% or less, and in surfaces of the external additive particles analyzed by X-ray photoelectron spectroscopy, relative to a total number of carbon atoms, nitrogen atoms, oxygen atoms, silicon atoms, and sulfur atoms, a ratio of a number of the nitrogen atoms is 0.40% or more and 2.50% or less, and a ratio of a number of the sulfur atoms is 0.05% or more and 0.25% or less.

External additive particles, toner, and method for producing external additive particles

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 includes: a fuel nozzle for injecting fuel; a combustion liner surrounding a combustion space for combusting the fuel and having an internal passage having an outlet communicating with the combustion space; and an air-fuel mixture line, connected to an inlet of the internal passage of the combustion liner, for introducing an air-fuel mixture containing the fuel and compressed air to the internal passage. The combustion liner is configured to be cooled by the air-fuel mixture flowing through the internal passage.

Combustor and gas turbine including the same

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.

A control device is a control device for a gas turbine including a plurality of combustors and is configured to select combustors to ignite in accordance with a target load on the basis of a predictor which defines a relationship between a load and the number and arrangement of combustors to ignite and a combustion temperature.

Control device, gas turbine, control method, and program

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

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 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 combustion burner includes a nozzle, a swirl vane having a fuel injection hole, the swirl vane being disposed in an air flow passage of an annular shape extending along an axial direction of the nozzle around the nozzle, and a partition plate having an annular shape and partitioning at least a region of the air flow passage in a radial direction of the nozzle, so as to divide at least the region into an inner flow passage facing an outer peripheral surface of the nozzle and an outer flow passage disposed on an outer side of the inner flow passage with respect to the radial direction. The fuel injection hole is disposed in the outer flow passage of the air flow passage. An end portion on an upstream side of the partition plate is disposed upstream of the fuel injection hole in the axial direction.

Combustion burner, combustor, and gas turbine

A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

Combustion burner, combustor, and gas turbine having a swirl vane with opposite directed surfaces

A fuel spray nozzle provided with: a liquid fuel channel (), which is a channel for liquid fuel; a liquid fuel injection hole (), which is a hole for communicating the liquid fuel channel () and the inside of a combustion burner, and injecting the liquid fuel into the combustion burner; an additive channel (), which is a channel for an additive; and an additive injection hole (), which is a hole for communicating the additive channel () and the inside of the combustion burner, and injecting the additive into the combustion burner at an angle at which the additive collides with the liquid fuel injected from the liquid fuel injection hole ().

Fuel spray nozzle

A toner according to the present disclosure maintains high transfer efficiency for the long term and obtains images which are not affected by toner base particles easily, which exhibit excellent charge stability, and which exhibit less fogging, wherein the toner is obtained by making inorganic fine particles and charge control particles, which satisfy specific conditions, present on the surfaces of toner base particles so as to satisfy a specific coverage relationship.

Toner

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

The present invention can provide a liquid developer that can accommodate faster process speeds by image forming apparatuses, in which the liquid developer contains a toner particle comprising a polyester resin, and a carrier liquid having a vinyl ether compound. The liquid developer further contains a polymer compound having a structural unit represented by formula (1) in either of the toner particle or the carrier liquid. 

Liquid developer

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

Growing community of inventors

Tokyo, Japan

Kei Inoue