Kawasaki Jukogyo Kabushiki Kaisha

B&b Agema Gmbh

Masahide Kazari

Atsushi Horikawa

Karsten Kusterer

Kunio Okada

Hidenori Arisawa

Ryozo Tanaka

Takao Sugimoto

Dieter Bohn

Hideyuki Imai

Tatsuhiko Goi

Kenichiro Tanaka

Takeo Oda

Seiji Yamashita

Tomoki Taniguchi

Junichi Kitajima

Akihito Abe

Hiroyuki Kashihara

Anis Haj Ayed

Harald Funke

Takeshi Horiuchi

Gang Lin

Nurettin Tekin

Anas Elyas

Kazuki Koga

A gas turbine combustor including a fuel injector having a plurality of annular fuel injection portions in each of which multiple fuel injection holes are formed, is provided with: an auxiliary fuel introduction passage for introducing an auxiliary fuel that is to be supplied to an auxiliary fuel injection portion that is a part of the plurality of annular fuel injection portions, into the fuel injector; a first main fuel introduction passage provided with a flow regulating valve for introducing a main fuel that is to be supplied to a main fuel injection portion that is an annular fuel injection portion other than the auxiliary fuel injection portion, into the fuel injector; and a second main fuel introduction passage provided with a flow regulating valve for introducing the main fuel that is to be supplied to the auxiliary fuel injection portion, into the fuel injector.

Gas turbine combustor and operating method thereof

A combustor includes: a combustion liner having a combustion chamber formed therein; and a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide grooves that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

Combustor for gas turbine engine

A fuel injection nozzle () of the present invention comprises a pre-mixing passage () which mixes fuel () and air () to generate an air-fuel mixture; and an injection port () which is located downstream of the pre-mixing passage () and injects the air-fuel mixture into a combustion chamber (). The fuel injection port () has a slit shape and a width that is less than a dimension that is twice as large as a quenching distance.

Fuel injection nozzle, fuel injection module and gas turbine

An aircraft engine apparatus () includes: a rotating shaft (); a fan () driven by the rotating shaft; a fan case surrounding the fan from outside in a radial direction of the rotating shaft; a nose cone () disposed upstream of the fan; a casing () that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter () that transmits motive force of the rotating shaft to the fan; and a support member () disposed inward of the first motive force transmitter in the radial direction, the support member coupling the nose cone to the casing such that the support member supports the nose cone in a stationary state.

Aircraft engine apparatus

In a continuously variable transmission including: a first transmission unit including a first input disc and a first output disc; and a second transmission unit disposed such that a back surface of a second input disc is opposed to a back surface of the first input disc, an input gear shroud covering an input gear disposed between the back surfaces of the first and second input discs, a first input disc side surface shroud integrally provided to a first input disc support supporting the first input disc on a housing of the continuously variable transmission, and a second input disc side surface shroud integrally provided to a second input disc support supporting the second input disc on the housing of the continuously variable transmission, are provided.

Toroidal continuously variable transmission

A toroidal-type stepless transmission includes: at least a pair of an input disc and an output disc; a power roller tiltably provided between the pair of the input disc and the output disc, the power roller being configured to transmit a driving force from the input disc to the output disc; and disc shrouds covering the input disc and the output disc, respectively. Each of the disc shrouds has an outer peripheral portion formed with an oil discharge groove configured to discharge an oil within each disc shroud to the outside, the oil discharge groove penetrating from an inner surface of the disc shroud to an outer surface of the disc shroud and extending in a circumferential direction of the disc shroud.

Toroidal-type stepless transmission

A fuel injector () comprises a cylindrical passage () which opens in a combustion chamber (), a fuel introduction passage () which guides fuel to a region of the cylindrical passage () which is closer to the combustion chamber (), and an air introduction passage () which guides compressed air to the cylindrical passage () at a location that is upstream of a location at which the fuel is introduced to the cylindrical passage (), wherein the fuel introduction passage () guides the fuel in a tangential direction of the cylindrical passage () in a transverse sectional view.

Fuel injector and gas turbine

The gas turbine system (GT) includes a combustor () having a fuel injection nozzle assembly () for jetting hydrogen gas (H) and pure water (W), a reservoir () for pooling the pure water (W) to be supplied to the combustor (), a gas compressing device () for boosting the hydrogen gas (H) to be supplied to the combustor (), a fuel supply passage () for guiding the boosted hydrogen gas (H) towards the combustor (), and a pressurizing passage () communicating between the reservoir () and the fuel supply passage () for pressurizing the pure water (W) by means of the boosted hydrogen gas (H).

Gas turbine system with injection water pressurization passage

In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.

Turbine blade cooling structure

A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.

Double-jet film cooling structure and method for manufacturing same

Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.

Growing community of inventors

Akashi, Japan

Masahide Kazari