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WO/2017/170784A1 |
A combustor (3) for mixing and burning fuel gas, water vapor, and air, and used in a gas turbine, said combustor being equipped with: a fuel injection device (13) having a fuel injection unit (33) that directly injects the fuel gas (H) i...
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WO/2017/170227A1 |
Provided is a combustor equipped with: a nozzle main body (16) having a shaft body (24) extending along an axial line, and swirl blades (26) that extend from the outer circumferential surface of the shaft body (24) in the radial directio...
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WO/2017/170476A1 |
A combustor (3) is provided with: a fuel nozzle for injecting fuel; a tubular body (24) that has a tubular shape in which a combustion region through which combustion gas flows is formed inside, and in which a plurality of slits (50) are...
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WO/2017/169950A1 |
This gas turbine combustor is provided with: a plurality of swirling cylinders (31) that are arranged within a combustor liner (11) and that impart a swirling flow to a premixed gas (Fp) comprising fuel and combustion air mixed in advanc...
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WO/2017/170209A1 |
Provided is a gas turbine in which a first nozzle (1) comprises first nozzle inner diameter-side fuel injection holes (13) for injecting a first nozzle fuel and first nozzle outer diameter-side fuel injection holes (14) that are for inje...
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WO/2017/165611A1 |
The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending...
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WO/2017/165581A1 |
The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle por...
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WO/2017/165092A1 |
The present disclosure is directed to an annular combustion system. The annular combustion system includes an inner liner and an outer liner that define there between an annulus that circumscribes a centerline of the combustion system. T...
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WO/2017/157631A1 |
The invention relates to a combustion chamber (18) of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy, said combustion chamber comprising a housi...
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WO/2017/158038A1 |
In accordance with one embodiment, a system is presented. The system includes a casing (36), a combustor (12) disposed within the casing (36), and a sensing device (38) located on the casing (36) and configured to sense a plurality of ac...
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WO/2017/158636A1 |
A gas turbine apparatus 10 according to an embodiment is provided with: a combustor casing 70; a combustor 20 disposed in the casing; a tubular body 80 surrounding the combustor 20 and demarcating a space between the combustor casing 70 ...
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WO/2017/154976A1 |
A fuel control device equipped with a trunk fuel valve degree-of-opening determination unit, a branch line flow rate determination unit, and a correction amount determination unit. The trunk fuel valve degree-of-opening determination uni...
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WO/2017/154900A1 |
A gas turbine combustor and a gas turbine, wherein there are provided a combustor outer cylinder (41), a combustor inner cylinder (42), a pilot nozzle (53) and a main nozzle (56) disposed in the combustor inner cylinder (42), an air chan...
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WO/2017/155914A1 |
A ducting arrangement (30) in a combustion system of a gas turbine engine is provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-ac...
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WO/2017/154821A1 |
This burner assembly of a combustor is equipped with: a plurality of first nozzles arranged in the circumferential direction of the combustor; a plurality of first burner cylinders which accommodate the plurality of first nozzles; and in...
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WO/2017/154729A1 |
In the present invention multiple cooling flow paths (35) are formed between the outer surface and the inner surface of a combustor panel. The cooling flow paths (35) have inlets (36i) that open at the outer surface and introduce a cooli...
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WO/2017/148843A1 |
The invention relates to a flow element (1) for fluidic contact with a hot gas flow (15) within an aircraft engine, wherein the flow element (1) comprises a base material (2), which has a hot gas surface (12) facing the gas flow (15) and...
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WO/2017/150419A1 |
This combustor (3) comprises: a first cylindrical body (11) that holds a fuel nozzle that extends in the direction of an axial line (Ac), and that has air flowing therethrough toward the downstream side; a second cylindrical body (12) th...
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WO/2017/150364A1 |
A combustion device is provided with a nozzle casing that defines an axial channel, and a nozzle disposed inside the axial channel. The nozzle includes: a cylindrical nozzle body extending along the axial channel; a swirler vane projecti...
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WO/2017/150664A1 |
This acoustic device (4) is provided with: a porous plate (32) having, on one plate-thickness-direction side, a plurality of holes (34) which pass through in the plate thickness direction and through which a main current flows; and a hou...
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WO/2017/142707A1 |
A method for predicting an anomaly in a combustor (16) is presented. The method includes receiving signals representative of parameters in one or more combustion cans (22, 24) of the combustor, generating a plurality of patterns based on...
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WO/2017/141510A1 |
Provided is a joined structure that has joining sections 15 in which a plurality of cylinders 11, 12 formed of a ceramic-based composite material are joined with each other via intermediate materials 16 by abutting end surfaces 11B, 12A ...
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WO/2017/139222A1 |
A fuel injector (32) for a combustion engine (10) includes an injector body (34) having formed therein a first passage (50) structured to feed a fuel to an outlet (40) of the injector body (34), and a second passage (52) structured to fe...
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WO/2017/138813A1 |
The invention provides an assembly (100) for the injection of fuel into the combustion chamber of an internal combustion engine comprising an actuator (1) with a drive shaft (2), an engagement means (4), and a rotary fuel injector compri...
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WO/2017/134843A1 |
An aviation component (1) used in an aviation gas turbine engine, wherein the aviation component (1) is provided with: an annular part (5) having an outer peripheral surface; a flange part (6) formed at one axial end part of the annular ...
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WO/2017/133819A1 |
The invention relates to a gas turbine combustion chamber comprising an inner combustion chamber wall (2) and an outer combustion chamber wall (3) that form an annular combustion chamber; air blending holes (4) are distributed along the ...
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WO/2017/134844A1 |
Provided is an aircraft component used in a gas turbine engine for an aircraft, the aircraft component comprising an annular part having an outer peripheral surface, and a boss part (7) that radially protrudes from the outer peripheral s...
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WO/2017/127255A1 |
A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straigh...
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WO/2017/121872A1 |
The present invention relates to a combustor (100) for a gas turbine, comprising: a pre-combustion chamber (101) having a peripheral wall (115) around a centre axis (35) of the pre-combustion chamber (101), the peripheral wall (115) comp...
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WO/2017/123982A1 |
A catalytic ignition system (10) includes a gas fuel supply (12) and a catalytic igniter (14) that is in fluid communication with the gas fuel supply. The catalytic igniter comprises a metallic shell (18), a catalyst (20) disposed within...
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WO/2017/123619A1 |
A fuel nozzle assembly includes a center body comprising an outer sleeve and an internal fuel passage defined within the outer sleeve. Tire internal fuel passage defines a fuel flow path within the center body and includes an inlet defin...
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WO/2017/120039A1 |
A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes two primary tubes, a secondary tube (603), a primary gas gallery (643), and a secondary gas gallery (644). The two primary tubes are conn...
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WO/2017/120037A1 |
A center body assembly (700) for a fuel injector (600) is disclosed. The center body assembly (700) defines a primary liquid passage (721), a liquid gallery, swirl slots (775), and a prefilm passage (769). The primary liquid passage (721...
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WO/2017/119993A2 |
Can-annular burners (28, 50) for gas turbine engines (20) with flow conditioners (42, 62, 72, 82) having locally varying, asymmetrical patterns of circumferential perforations (44, 64), to promote uniform fuel-air mixture among all premi...
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WO/2017/120035A1 |
A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes a flange assembly (610) with a distribution block (612), three main gas tubes, and an injector head (630). The distribution block (612) e...
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WO/2017/120038A1 |
A method for lean direct injection of a liquid fuel from a fuel injector (600) into a combustion chamber (390) of a gas turbine engine (100) is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber (...
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WO/2017/116243A1 |
A combustor assembly lift track comprises one or more rails comprising one or more portions that combine to extend in a non-linear path and a rail connector attached to at least one of the one or more portions of the one or more rails, w...
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WO/2017/116242A1 |
A combustor assembly lift arm (220) comprises a moveable support arm comprising a first end and a second end with a combustor assembly engagement frame (240) connected to the first end of the moveable support arm, wherein the combustion ...
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WO/2017/116266A1 |
A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel por...
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WO/2017/116244A1 |
A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combus...
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WO/2017/110971A1 |
This gas turbine engine (GE), which burns, in a combustion chamber (3), a compressed gas compressed by a compressor (1), and drives a turbine (5) by means of the obtained combustion gas, is provided with: a compressed gas supply part (17...
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WO/2017/110955A1 |
A fuel injection device (1) for injecting a mixture of fuel and air into a combustion chamber (E) inside the combustor (CB) of a gas turbine engine, wherein the fuel injection device (1) is provided with a fuel injection valve (3) having...
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WO/2017/111262A1 |
A streamer induction type combustor for improving flame stability according to one embodiment of the present invention may comprise: a combustion chamber in which combustion occurs; a high voltage supply which is installed outside the co...
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WO/2017/110973A1 |
A gas turbine engine (GT) provided with: a plurality of combustors (3) disposed at an incline toward the radially outward side from the turbine side toward the compressor side; and a diffuser inner tube (25) and outer tube (27) forming a...
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WO/2017/110104A1 |
The present invention reduces the thermal stress of flanges which join a combustor casing and a turbine casing together. This gas turbine (10) is provided with a compressor (14), a combustor (15), and a turbine (16) along the extension d...
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WO/2017/108454A1 |
The present invention relates to a combustor (100) for a gas turbine comprising: a pre-combustion chamber (101), a swirler (103), a pilot burner (110) upstream the pre-combustion chamber (101) which comprises a pilot burner surface (111)...
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WO/2017/111889A1 |
A gas turbine engine has attached thereto a transducer (45) for transmitting ultrasonic waves through the premix injector (10) and the combustion chamber (35). The transducer (45) may be a piezoelectric transducer. Ultrasonic waves may b...
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WO/2017/111041A1 |
The main fuel injection section of a fuel injection device has: a main outer air flow passage for taking in compressed air from an inlet open radially outward; a main inner air flow passage for taking in compressed air from an inlet open...
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WO/2017/103232A1 |
In order to provide a combustion chamber device which is easy to produce and allows a reliable operation, it is proposed that the combustion chamber device comprises the following: a burner head for the supply of fuel and/or oxidator to ...
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WO/2017/098782A1 |
This fuel cell system is provided with: a fuel cell; an electric compressor that supplies a cathode gas to the fuel cell; a cathode exhaust gas passage through which flows a cathode exhaust gas discharged from the fuel cell; a turbine pr...
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