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Matches 1 - 50 out of 12,145

Document Document Title
WO/2018/009418A1
A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surfa...  
WO/2018/009411A2
A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combu...  
WO/2018/003488A1
This gas turbine combustor comprises: a casing which is coupled to a main housing; a liner which has an interior in which a combustion chamber extending in the axial direction is formed, the liner comprising an upstream portion, includin...  
WO/2018/004097A1
The present invention relates to: a transition piece assembly having improved cooling efficiency for cooling a high-temperature region formed on the side surface of a transition piece; and a combustor including the same, and provides a t...  
WO/2018/001696A1
The invention relates to a heat shield assembly (01) of a combustion chamber, comprising a supporting structure (03) and heat shield elements (11) arranged on the supporting structure (03). For fastening, the supporting structure (03) ha...  
WO/2017/218217A1
The present disclosure is directed to a fuel injector assembly of a gas turbine engine, including a centerbody, an outer sleeve surrounding the centerbody, an inner sleeve disposed between the centerbody and at least a section of the out...  
WO/2017/217622A1
The present invention relates to an air guide cap for guiding airflow to a through hole on the bottom. The air guide cap comprises: an upper surface upwardly inclined with respect to a horizontal plane; and wall surfaces extending downwa...  
WO/2017/213113A1
Corrosion resistance is enhanced while ensuring high enough heat shielding performance and erosion resistance. The present invention is provided with: a highly porous layer (6) that is formed on a heat-resistant substrate (100), that is ...  
WO/2017/209127A1
Provided is a structure that cools a constituent member (5) of a gas turbine (GT) using a working gas (A), wherein: a plurality of heat transfer enhancement ribs (15), each in the shape of a letter W, are provided protruding from a wall ...  
WO/2017/207573A1
The fuel nozzle (1) for the gas turbine (1) comprises a radial swirler (111) and an axial swirler (121). The radial swirler (111) is arranged to swirl a first flow (A1+F1) of a first oxidant-fuel mixture and the axial swirler (121) is ar...  
WO/2017/207902A1
The invention relates to an inlet body (3) for a fluid injector (1) for a turbomachine. The inlet body (3) comprises a casing (30) defined by an internal surface (31) and a seal valve (6) housed inside the casing (30). The valve (6) comp...  
WO/2017/207301A1
The invention relates to a combustor arrangement (1), the combustor arrangement (1) being annular and being arranged about an axis, the axis defining an axial direction (A), comprising an annular housing (2) to house a plurality of burne...  
WO/2017/207901A1
The invention relates to an inlet body for a fluid injector for a turbomachine. The inlet body comprises a casing and an inlet nozzle (50), housed inside the casing, and configured to serve as a seat for a mobile sealing member (20). The...  
WO/2017/204229A1
A combustor (3) is provided with: a fuel nozzle that extends along an axial line Ac; an inner cylinder (41) that has a cylindrical shape and covers the fuel nozzle; and a tail cylinder (42) that has a cylindrical shape extending toward t...  
WO/2017/204949A1
A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tu...  
WO/2017/203145A1
Annular combustion chamber of continuous detonation wave type enabling, from a mixture of a fuel and an oxidiser injected in an axial direction F, the delivery of a continuous production of hot gases from the detonation waves, the combus...  
WO/2017/197544A1
Four aeronautic/astronautic turbofan engines, which are respectively a turbofan engine comprising an air inlet for introduction of oxygen-enriched air, a turbofan engine comprising two oxygen-enriched air inlets, a turbofan engine free o...  
WO/2017/200678A1
The present application provides a selective catalyst reduction system for use with a combustion gas stream of a gas turbine. The selective catalyst reduction system may include a tempering air system with a finger mixer and a number of ...  
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/2017/165876A3
A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner ...  

Matches 1 - 50 out of 12,145