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Matches 1 - 50 out of 12,058

Document Document Title
WO/2017/196356A1
A method, including: operating an industrial gas turbine engine having a plurality of combustor cans (100) arranged in an annular array, each can having burner stages (122, 124, 132) and a pilot burner arrangement (104) having a premix p...  
WO/2017/196208A1
The group of inventions is intended to improve the energy efficiency of internal combustion engines by improving the conversion of fuel combustion energy into mechanical energy. The claimed method is characterized in that, in a working c...  
WO/2017/195518A1
Provided is a coating structure, a turbine part having the same, and a method for manufacturing the coating structure. The coating structure is provided on a surface of a base portion including a ceramic-based composite material. The coa...  
WO/2017/194886A1
The present invention relates to a composite part comprising at least: - a fibrous reinforcement comprising silicon carbide fibers having an oxygen content of less than or equal to 1% as an atomic percentage, and - a matrix present in th...  
WO/2017/190967A1
A combustor assembly includes a combustion liner having a longitudinal axis and defining a combustion chamber, a flow sleeve housing the combustor liner, a casing housing the flow sleeve, and a plurality of impingement plates. The combus...  
WO/2017/192147A1
A gas turbine engine has a flow metering device located between the combustor and the transition duct. The flow metering device engages the transition duct with a spring device. The flow metering device meters the airflow and axially cen...  
WO/2017/192354A1
An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure th...  
WO/2017/187104A1
An air intake swirler (100, 200) for a turbomachine injection system (70) comprises an upstream wall (102, 202) and a downstream wall (104, 204), both of revolution about an axis (44) of the air intake swirler, and fins (106, 206) distri...  
WO/2017/188039A1
The present invention reduces pressure loss in compressed air that is supplied from a compressor to a combustion cylinder. A compressor diffuser (5), wherein one end (51) thereof is connected to an exit port (16) of a compressor (1), the...  
WO/2017/188052A1
The integrated gasification combined cycle power generation plant comprises: a gasification furnace; a gas turbine which is configured to be drivable by using combustible gas generated by the gasification furnace as fuel; a flow rate con...  
WO/2017/186386A1
Burner component, burner, and methods of manufacturing or operating of these for dual fuel operation The invention is related to a burner, a burner component (10) and to methods of manufacturing and operation, in which the burner compone...  
WO/2017/182658A1
A swirler (60) for mixing fuel with air in a combustion engine (10) is disclosed. The swirler (60) comprises a central axis (63), a swirler base (61) comprising an upper surface (62), a central portion (64), a number of main swirler elem...  
WO/2017/178736A1
Gas turbine combustion chamber injector (1), comprising – a fluid supply system (5), – an injector body (4) extending along a longitudinal axis (Z-Z), – an injection head (6) arranged on the injector body (4) and configured in such...  
WO/2017/180295A1
A fuel injector (26) for a combustion engine (10) includes an injector head (28) including a nozzle (44), a premixer (48), and a distributor (70) structured to distribute a plurality of different fuels to different sets of fueling orific...  
WO/2017/180294A1
A fuel injector (26) for a combustion engine (10) includes an injector head (28) including a nozzle (44), a premixer (48), and a distributor (70) structured to distribute a plurality of different fuels to different sets of fueling orific...  
WO/2017/180296A1
A fuel injector (26) for a combustion engine (10) includes an injector head (28) including a nozzle (44), a premixer (48), and a distributor (70) structured to distribute a plurality of different fuels to different sets of fueling orific...  
WO/2017/175918A1
One embodiment of the present invention provides a combustor having excellent performance with respect to high-efficiency and low-emission combustion since a flame is formed by optimizing a divided-flame technology, an air-staged technol...  
WO/2017/175958A1
An industrial combustor is disclosed. The present invention comprises: a housing; a first injection nozzle provided such that a part thereof is inserted into the housing, and supplying pilot fuel to the housing; and a second injection no...  
WO/2017/175471A1
In the present invention, a molding material which is a mixture of a metal powder and a binder is melted and injection molded (primary molding) into an injection mold, thereby creating an injection molded body 10A, 110A, 210A, 310A, 410A...  
WO/2017/170485A1
A combustor (3) is provided with: a first nozzle (51) extending along an axis (Ac) and injecting fuel to the downstream side; a flame stabilizer (52C) for covering the downstream end of the first nozzle (51) from the outer peripheral sid...  
WO/2017/172408A1
Injector assembly and ducting arrangement including such assemblies for a combustor system in a gas turbine engine are provided. A reactant-guiding structure (42) may be configured to define a curvilinear flow path (47) to route a flow o...  
WO/2017/170834A1
Provided is a combustor comprising: a nozzle body (16) having a shaft body (24) extending along an axis, the shaft body (24) having a purge air flow passage (29) formed therein so as to extend along the axis to the front end of the shaft...  
WO/2017/170477A1
A gas turbine (1) has: a compressor (2) for generating compressed air; a wheel casing (5) into which the compressed air is introduced; a combustor (3) for generating combustion gas; a turbine (4) driven by the combustion gas; a combustor...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  
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...  
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 ...  
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 ...  
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...  

Matches 1 - 50 out of 12,058