Japan Aerospace Exploration Agency

Kawasaki Jukogyo Kabushiki Kaisha

Osaka Gas Company Limited

Kazuo Shimodaira

Kazuaki Matsuura

Takeshi Yamamoto

Yuji Nakamura

Hitoshi Fujiwara

Hideshi Yamada

Shigeru Hayashi

Masamichi Ippommatsu

Takeo Oda

Atsushi Horikawa

Masayoshi Kobayashi

Ryusuke Matsuyama

Seiji Yoshida

Seiichi Ito

Koji Moriya

Tsutomu Wakabayashi

Takahiro Sako

Shonosuke Koga

Yoji Kurosawa

Youji Kurosawa

Kazuo Suzuki

A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the main injector includes: a first inflow channel through which the air having a major flow component in an axial direction is taken; a second inflow channel through which the air having a major flow component in a radial direction is taken and which causes the air therein to meet the air from the first inflow channel; and a main fuel injecting portion configured to inject the fuel only to the second inflow channel.

Fuel injector with radial and axial air inflow

A fuel injector includes: a pilot injector configured to spray fuel so as to form a first combustion region in a combustion chamber; and a main injector provided coaxially with the pilot injector so as to surround the pilot injector and configured to supply a fuel-air mixture that is a mixture of the fuel and air to form a second combustion region in the combustion chamber, wherein the pilot injector includes: a center nozzle configured to eject air jet flowing straight in an axial direction on a central axis of the pilot injector; an inside swirler provided on a radially outer side of the center nozzle and configured to cause inflow air to swirl around the central axis; and a pilot fuel injecting portion configured to inject the fuel from between the center nozzle and the inside swirler to air flow in the center nozzle.

Pilot fuel injector with swirler

The object of the invention is to provide a lightweight mechanism that changes the distribution of a flow rate of air for combustion supplied into each burner, without providing a mechanical movable part in a passage for high-temperature and high-pressure air for combustion in a combustor having a plurality of burners such as a pilot burner and a main burner. The combustor equipped with an air flow rate distribution control mechanism based on a fluidic element in accordance with the present invention has a plurality of burners such as a main burner and a pilot burner, wherein with the fluidic element being disposed upstream of a passage of air for combustion that is supplied to each burner, and means for sucking out or blowing out air into a control air passage of the fluidic element being provided, the distribution of a flow rate of the air flowing into the burners is controlled by changing a flow direction of the air for combustion.

Combustor equipped with air flow rate distribution control mechanism using fluidic element

A main swirler of a triple annular configuration that is partitioned by a pre-filmer and a separator is installed in an inlet port of a main air flow channel. The vicinity of the inner wall of the main air flow channel provided with a main fuel injection port is bulged radially outward from the innermost surface (innermost surface of a small swirler) of a main swirler. Further, a distance from the main fuel injection port and the pre-filmer is set such that an effective opening area between the pre-filmer and 'the inner wall of the main air flow channel provided with the main fuel injection port' is equal to an effective opening area of the small swirler. The swirling directions of the swirlers of the main swirler are 'clockwise'-&#x201c;counter-clockwise&#x201d;-&#x201c;clockwise&#x201d; respectively along the radial outward direction when the swirling direction of the innermost swirler is taken as &#x201c;clockwise&#x201d;.

Staging fuel nozzle

Disclosed is a burner apparatus comprising an inner tube defining a second channel and an outer tube defining a first channel surrounding the inner tube, air supplying means for supplying air to the first channel and the second channel, and gas supplying means for supplying fuel gas to the first channel and the second channel, either the first channel or the second channel being used as a main combustion channel and the other being used as a pilot combustion channel, the main combustion channel and the pilot combustion channel receiving the supply of fuel gas for combusting it. A plurality of first supply openings for supplying the fuel gas into the main combustion channel are distributed in the main combustion channel in a direction away from the pilot combustion channel. Discharging resistance of the fuel gas from each first supply opening due to passage of the oxygen-containing gas is set so as to increase as being distant from the pilot combustion channel.

Fluid distributor, burner apparatus, gas turbine engine and co-generation system

A fluid distributor includes a first feed port for feeding fuel gas into a main fuel flow path, a feed path for feeding the fuel gas inside a gas flow path to the first feed port, and distributedly into a pilot fuel flow path so as to increase the distribution ratio of the fuel gas to the first feed port according to an increase in an overall feed flow rate of the fuel gas from the gas flow path to a feed path and, inversely, to decrease the distribution ratio of the fuel gas to the first feed port according to a decrease in the overall feed flow rate. A plurality of fluid distributors are disposed in the main fuel flow path and pilot fuel flow path distributedly in the peripheral direction to constitute a gas feed means.

Fluid distributor, burner device, gas turbine engine, and cogeneration system

Growing community of inventors

Chofu, Japan

Kazuo Shimodaira