Kawasaki Jukogyo Kabushiki Kaisha

Japan Aerospace Exploration Agency

Hideki Ogata

Takeo Oda

Atsushi Horikawa

Masayoshi Kobayashi

Ryusuke Matsuyama

Hiroyuki Ninomiya

Kenta Yamaguchi

Kazuhiko Ohyama

Tomoyuki Hatano

Akihiro Shimizu

Touya Miwa

Hitoshi Fujiwara

Takeo Nishiura

Yoshiharu Nonaka

Tohru Imamura

Kunio Hidani

Atushi Horikawa

A fuel injection device includes: a pilot fuel injector disposed at a radially center position; a main fuel injector having an annular shape and disposed so as to encircle the pilot fuel injector; a fuel injection portion that injects a fuel into a combustion chamber; a fuel supply unit that supplies a fuel to the fuel injection portion; a fuel introduction portion secured to a combustor housing that has the combustion chamber therein and introduces a fuel into the fuel supply unit; and an injector housing that is supported by the fuel introduction portion and covers front portions of the pilot fuel injector and the main fuel injector. The fuel supply unit has a base supported by the fuel introduction portion, and an annular body supported by the injector housing via a support pin so as to be radially movable relative to the injector housing.

Fuel injection device

A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure. In addition, the fuel divider includes an adjusting means which adjusts a value of the first pressure in such a manner that it applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force.

Fuel supply device of gas turbine engine

In a fuel supply device of a gas turbine engine of the present invention, a fuel dividerincludes a fuel entrance Einto which the fuel supplied from a collecting fuel passageis introduced; a pilot portconnected to the pilot fuel passage; a main portconnected to the main fuel passage; a pilot port needle valve elementwhich adjusts an opening degree of the pilot port; a main port needle valve elementwhich opens and closes the main port; and a drive elementwhich is actuated according to the fuel pressure at the fuel inlet Eto drive the pilot port needle valve elementand the main port needle valve element

A fuel supply device of a gas turbine engine is provided. The fuel supply device includes a fuel divider which divides fuel supplied from a collecting fuel passage to feed the fuel to a pilot fuel passage and to a main fuel passage. The fuel divider includes a movable member which is movable according to fuel pressure at the fuel entrance and opens and closes pilot ports and main ports according to a distance of the movement of the movable member. When the fuel pressure at the fuel entrance is not higher than a predetermined value, the fuel is supplied only to the pilot fuel passage, while when the fuel pressure at the fuel entrance is higher than the predetermined value, the fuel is supplied to the pilot fuel passage and to the main fuel passage.

The present invention provides a fuel spray apparatus for a gas turbine engine, including: a pilot part configured to spray a fuel to be used for a diffusion combustion; a main part provided so as to surround the pilot part and configured to inject a pre-mixed gas only upon a high power operation; and a shield body constituting a purge air passage which is configured to take therein an air flowed on an upstream side relative to a fuel injection port of the main part as a purge air, and to blow off a fuel dripping from the fuel injection port toward a main air passage of the main part. The purge air passage is provided in a position opposite to a main fuel passage communicated with the fuel injection port across the shield body.

Fuel spray apparatus for gas turbine engine

A gas turbine combustor of the present invention comprises a fuel injector for injecting a fuel toward a combustion chamber; a swirler which takes-in compressed air generated in a compressor and swirls the compressed air, in the vicinity of the fuel injector; a tubular guide member for guiding the compressed air taken-in from the swirler, to the combustion chamber; and a heat shield having a cylindrical portion located outward relative to the guide member; wherein the cylindrical portion has a purge hole; and air is introduced through the purge hole and is supplied to a space formed between the guide member and the cylindrical portion.

Gas turbine combustor

The present combustor of gas turbine engine includes: a fuel injection unit including a fuel spray part to spray a fuel so that a diffusion combustion region is formed in a combustion chamber, and a pre-mixture supply part to supply a pre-mixture of a fuel and an air so that a pre-mixture combustion region is formed in the combustion chamber; and a fuel supply unit to supply the fuel to the fuel spray part and pre-mixture supply part. The fuel supply unit includes: a pilot fuel passage and a main fuel passage to supply the fuel to the fuel spray part and the pre-mixture supply part, respectively; an assembled fuel passage to supply the fuel to the pilot and main fuel passages; and a fuel distributor disposed at a branch point where the assembled fuel passage is connected to both the pilot and main fuel passages. The fuel distributor is configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with the fuel pressure.

Combustor of a gas turbine engine

A gas turbine combustor, which can enable only a swirler and a heat shield to be readily taken out from the combustor upon the exchange the swirler and the heat shield. The gas turbine combustor includes: a combustion cylinder; a fuel injection unit for supplying fuel to a head portion of the combustion cylinder; a support member configured for allowing the fuel injection unit to be supported by the combustion cylinder; and a heat shield adapted for heat-insulating the support member from combustion gas in the combustion chamber, wherein the fuel injection unit includes a fuel injection valve for injecting the fuel, and a swirler for supplying compressed air to the fuel injected from the fuel injection valve while swirling the compressed air. The swirler and heat shield are connected together, constituting a swirler unit. This swirler unit is detachably attached to the support member via a fastening member.

Gas turbine fuel injector mounting system

A fuel spraying apparatus of a gas turbine engine includes a first fuel spraying section configured to spray fuel for diffusion combustion and a second fuel spraying section configured to spray fuel for premixed combustion. The second fuel spraying section is disposed so as to surround the first fuel spraying section. The apparatus further includes an air curtain generating section disposed between the first fuel spraying section and the second fuel spraying section. The air curtain generating section is configured to generate an air curtain which defines an outer edge of a diffusion combustion area in a combustion chamber.

Fuel spraying apparatus of gas turbine engine

A combustor of gas turbine engine, including: a fuel spray portion that sprays fuel to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion that atomizes the fuel, and a diffusion passage portion disposed downstream of the fuel atomizing portion, the diffusion passage portion having a spreading trumpet-like shape and diffuses the fuel and the air; a pre-mixture supply portion that supplies a pre-mixture gas including the fuel and air to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion to surround the fuel spray portion; and a fuel diffusion restraining member disposed on an inner circumferential face of the diffusion passage portion for restraining a diffusion of injected fuel by separating a stream of the injected fuel away from the inner circumferential face.

Growing community of inventors

Kakogawa, Japan

Hideki Ogata