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WO/2018/041647A1 |
The invention is directed to a burner (1) of a turbomachine, particularly a gas turbine engine, comprising an upstream burner section (2) for providing a first fuel and/or an oxygen containing fluid to an upstream end of a burner interio...
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WO/2018/041454A1 |
The present invention relates to a turbine, in particular a turbine with heat exchanger for producing energy, in particular electrical energy, comprising at least one compression stage (12) with at least one gas compressor (14), a cross-...
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WO/2018/041455A1 |
The present invention relates to a combustion chamber (10) of a turbine, in particular a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, in particular electrical energy, comprising a casing (12) with an...
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WO/2018/044266A1 |
An impingement cooling system for a gas turbine engine includes an initial impingement surface (10) with a centrally located opening (12). A plurality of channels (14) and plurality of sub-channels (22) extends radially outward from the ...
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WO/2018/038792A1 |
A fuel-air mixer assembly (52) that includes a mixer portion, and a flare cup portion (60) coupled to the mixer portion. The flare cup portion includes a side wall (68) that including an inlet opening and a discharge opening (72) defined...
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WO/2018/025294A1 |
This combustor 20 comprises: a combustor liner 61 that is provided in a combustor casing 70; a cylindrical body 80 that partitions the space between the combustor casing 70 and the combustor liner 61; piping 42 that guides combustion gas...
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WO/2018/026579A1 |
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...
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WO/2018/026382A1 |
Injector assemblies (12) and ducting arrangement including such injector assemblies are provided. The injector assembly may include a reactant-guiding structure arranged to convey a flow of reactants (19) into the combustion stage and me...
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WO/2018/026381A1 |
A combustion system in a combustion turbine engine is provided. The system may include a combustor wall (40) fluidly coupled to receive a cross-flow of combustion products (21). The combustor wall (40) may include a plurality of cooling ...
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WO/2018/021996A1 |
A gas turbine engine has a resonator ring (10) that is formed by two circumferentially extending rings. The first and second circumferentially extending rings (30, 31) have located within them baffles (20). Both the first ring (30) and t...
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WO/2018/011827A1 |
A swirl mesh lean direct injection concept for distributed flame holding for low pollutant emissions and mitigation of combustion instability. The invention further relates to a new method for flame holding with least pressure drop and f...
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WO/2018/012327A1 |
The present invention provides a structure in which an operative gas (A) of a gas turbine engine (GT) is used as a cooling medium (CL) to cool a constituent member of the gas turbine engine, wherein a wall surface (13a) of a flow channel...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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