Kawasaki Jukogyo Kabushiki Kaisha

Japan Aerospace Exploration Agency

Ryusuke Matsuyama

Hitoshi Fujiwara

Masayoshi Kobayashi

Atsushi Horikawa

Takeo Oda

Takeo Nishiura

Kenta Yamaguchi

Hideshi Yamada

Shigeru Hayashi

Hideki Ogata

Kazuo Shimodaira

Kazuaki Matsuura

Youji Kurosawa

A fuel injector includes: a pilot fuel injection portion including a pilot fuel supply block and a pilot shroud; a main fuel injection portion arranged so as to surround the pilot fuel injection portion from an outer side in a radial direction; and an intermediate air passage arranged between the pilot fuel injection portion and the main fuel injection portion. The pilot shroud includes: a throat located at a downstream side of the pilot fuel supply block; and a flame holding portion surrounding flame located at the downstream side of the throat. An air injection slit is formed at the flame holding portion, the air injection slit being configured to inject compressed air of the intermediate air passage in a direction along an inner peripheral surface of the flame holding portion such that the compressed air covers the inner peripheral surface over an entire periphery.

Fuel injector

A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.

Fuel injection device

A fuel injection device for a gas turbine combustor includes a pilot fuel injector disposed on an axis of the fuel injection device; an annular main fuel injector encircling the pilot fuel injector; and a plurality of main fuel injection holes formed in the main fuel injector and spaced circumferentially from each other for injecting fuel axially rearward. The main fuel injector includes an annular fuel passage forming portion, an inner ring portion on an inner peripheral side of the fuel passage forming portion, and an outer ring portion on an outer peripheral side of the fuel passage forming portion. One of a space between the fuel passage forming portion and the inner ring portion and a space between the fuel passage forming portion and the outer ring portion forms a pilot fuel supply passage, and the other one forms a main fuel supply passage.

Fuel injecting device

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.

A fuel injection device for a gas turbine combustor includes: a pilot fuel injector; a main fuel injector; a plurality of main fuel injection holes arranged in the main fuel injector to inject the fuel rearward; a main fuel injection nozzle to guide the fuel to a main air passage, protruding rearward from a circumference of the main fuel injection hole into the opening formed in a passage wall that forms the main air passage; a heat-shielding casing covering the main fuel injector; and a ring member interposed in an axial gap between the passage wall and the heat-shielding casing. The ring member covers a through-hole gap between the main fuel injection nozzle and a through-hole in the heat-shielding casing, and has a purge passage communicated with the opening to introduce air into the main air passage.

A fuel injection device for injecting an air-fuel mixture to a combustion chamber in a combustor of a gas turbine engine includes a fuel injector which is arranged on an axis of the fuel injection device. The fuel injector includes a fuel injection portion for injecting fuel in the radial direction of the fuel injection device, a fuel flow path portion forming a passage through which fuel is supplied to the fuel injection portion, and a heat shield cover that covers an end portion facing toward the combustion chamber side of the fuel injection portion such that an air layer is formed between the heat shield cover and the end portion.

A fuel injection device for supplying a fuel to a compressed air includes: a pilot fuel injector; a main fuel injector located at an outer periphery of the pilot fuel injector; and an air injection unit located between an outlet end portion of the pilot fuel injector and the main fuel injector. The air injection unit includes: a partition wall plate separating the air injection unit from a combustion chamber; a flame stabilization plate provided at a downstream side of the partition wall plate; a first opening at a downstream side between the flame stabilization plate and the outlet end portion of the pilot fuel injector; and a second opening provided in the partition wall plate and through which the compressed air is supplied. The flame stabilization plate includes an inclined portion inclined in a radially outward and downstream direction with respect to an axis.

An annular type gas turbine combustor having a plurality of fuel nozzle assemblies () on a circumference includes a pilot nozzle unit () for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle () into a combustion chamber (), a main nozzle unit () provided so as to surround the pilot nozzle unit () for spraying a fuel for premix combustion, and a flow guide () disposed on a downstream side of each of the fuel nozzle assemblies () and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (), which gradually increase in a downstream direction.

Gas turbine combustor

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

A fuel injector includes a pilot fuel injector, configured to inject the fuel into a combustion chamber, and a main fuel injector provided coaxially with the pilot fuel injector so as to surround the pilot fuel injector and configured to have a main flow path to generate a premixed air-fuel mixture. The main flow path includes an outer main air passage located radially outwardly and configured to supply a compressed air in an axial direction into an annular premixed air-fuel mixture passage, an inner main air passage located radially inwardly and configured to supply the compressed air into the premixed air-fuel mixture passage from a radially inner side. The injector further includes a main fuel injection port to inject the fuel from an axially upstream side into the inner main air passage.

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.

Growing community of inventors

Akashi, Japan

Ryusuke Matsuyama