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Matches 1 - 50 out of 12,779

Document Document Title
WO/2019/194817A1
A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rota...  
WO/2019/185246A1
The invention relates to a moulded part made oxide composite fibre ceramic, referred to below as a "CMC moulded part", such as can be used, for example, in a turbine component, in a burner and/or in an exhaust gas system, in particular o...  
WO/2019/188484A1
This fuel supply device is provided with a first supply pipe (2f), a first on-off valve (V1), a second on-off valve (V1, V2), a second supply pipe (2d), a connecting pipe (2h), a third on-off valve (V3), and a leak check measuring device...  
WO/2019/188409A1
A combustion device (C) that uses combustion air to burn a fuel inside a combustion chamber (N). The combustion device (C) is equipped with a reducing agent injection device that has injection openings (2n) and that injects a prescribed ...  
WO/2019/185232A1
The invention relates to a fuel feed device (1) comprising: a fuel nozzle (2) having a fuel feed channel (3) extending in an axial direction and a plurality of fuel outlet channels (4), which branch off from said fuel feed channel, exten...  
WO/2019/188012A1
A combustion device (C) according to the present disclosure causes fuel to burn in a combustion chamber (N) using combustion air, and is provided with a reducing agent injecting portion (2e) which injects a reducing agent toward a flame ...  
WO/2019/187782A1
A fuel gas cooling system and a gas turbine plant are provided with: a gas cooler (39) which performs cooling by causing cooling water (CW) to come into contact with compressed fuel gas (FC) serving as a fuel gas; a cooling water dischar...  
WO/2019/187559A1
Provided is a combustor wherein flashback can be sufficiently suppressed while reducing NOx. This combustor comprises: a casing 20 having in the interior thereof an air chamber 121 filled with air; mixed flow path formation members 131, ...  
WO/2019/185736A1
A device for producing pressure waves of high amplitude, in particular for cleaning boilers, has a pressure-tight vessel (21, 40) comprising a burning chamber (121) introduced therein, which can be filled via feed lines with a flowable m...  
WO/2019/181188A1
This fuel nozzle for a gas turbine comprises: a nozzle body; a fuel injection opening formed in the nozzle body so as to have, on a one-end side, an injection port that opens in the outer surface of the nozzle body; and a fuel channel pr...  
WO/2019/181183A1
This fuel nozzle for a gas turbine, which injects fuel, is provided with: a purge gas line which extends in the axial direction of the fuel nozzle and which discharges purge gas from the downstream end, in the axial direction, of the pur...  
WO/2019/179691A1
The invention relates to a burner (1) with a control unit (11), a combustion chamber (10), a pressure sensor and fuel stages (2, 3, 5, 6, 8) which are arranged to supply fuel with a respective mass flow to the combustion chamber (10), wh...  
WO/2019/181877A1
This combustor (22) is provided with: a fuel supply section (35) defining on a radially inner side of an axis line (A) an inner periphery side space (34a) into which inert gas (E) is introduced and which supplies the inert gas (E) to a c...  
WO/2019/172925A2
A finely distributed combustion system for a gas turbine engine is provided. A combustor body (12) may extend along a longitudinal axis (14). A premixer space (21) may be formed within the combustor body to premix air and fuel. The premi...  
WO/2019/166400A1
The invention relates to a computer-implemented method for minimizing thermoacoustic, aeroacoustic and/or aeroelastic instability states of a combustion process in a gas turbine, wherein the gas turbine has a combustion volume comprising...  
WO/2019/166745A1
The invention relates to a combustion chamber for a gas turbine engine, the combustion chamber comprising a chamber bottom provided with an upstream wall (230) and a downstream wall (218) which extend between an inner annular wall and an...  
WO/2019/158323A1
The invention relates to a method for operating a burner arrangement (16) of a heat engine, particularly a gas turbine, comprising a plurality of burners (2), each one having at least one pilot burner (6) and at least one main burner (8)...  
WO/2019/141522A1
The invention relates to a component (1), which is designed to position a heat shield element (2) relative to a support structure (3) of a combustion chamber, in particular in the form of a brick holder or spring element, characterized i...  
WO/2019/135918A1
A gas turbine combustor assembly (200) includes: a primary combustion chamber (214) in fluid communication with a primary fuel outlet of a primary fuel injector (204); a torch igniter (212) coupled to the primary combustion chamber, the ...  
WO/2019/131429A1
This combustor is provided with: a combustor body (41) having a fuel nozzle for injecting fuel, and a combustor cylinder (44) through which combustion gas (G) generated from combustion of the fuel flows, and in which an outlet (45) that ...  
WO/2019/132326A1
The present invention comprises: an inner housing into which air flows; a first outer housing disposed so as to encompass an outlet part of the inner housing, and spaced from the inner housing such that the air flows therein; a second ou...  
WO/2019/126434A1
Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrol...  
WO/2019/117135A1
A fuel supply device provided with: a first motorpump (10) that discharges fuel at a first flow rate toward an engine (X); a second motorpump (18) that discharges fuel at a second flow rate and merges this fuel with the fuel of the first...  
WO/2019/115129A1
The invention relates to a combustion chamber (1) comprising a jacket (3) that is arranged around a principal axis (2) of the combustion chamber (1), and a ceramic tube (4) that is arranged inside the jacket (3), wherein an intermediate ...  
WO/2019/110210A1
A heat shield (60) for a gas turbine engine (10), the heat shield (10) comprising a main body (61) having a first surface (70) and a second surface (72), the first surface (70) being exposed to a hot working gas in use, a plurality of wa...  
WO/2019/107392A1
The present invention comprises: a cylindrical combustion tube (21) through which a combustion gas (B) flows; an introduction pipe (41) connected to the outer peripheral surface of the combustion tube (21) such that one end of the introd...  
WO/2019/104614A1
Disclosed is an oxidant-mutifuel burner capable of being used for solid fuel and gas fuel, the burner including: a flameproof unit (10), a metal member (20), a fuel-oxidant supply system (11) including a fuel burner and several fuel-oxid...  
WO/2019/107356A1
Provided is a burner device (1) that supplies a premixed gas (M) of a fuel gas (F) and a supporting gas (A) to a combustion region (R), the burner device (1) being provided with: slit-like injection ports (5) that are formed in a burner ...  
WO/2019/107355A1
A burner device (1) that supplies a mixed gas (MG) of a fuel gas (F) and a combustion-assisting gas (A) to a combustion region (R) and comprises: primary mixing passages (27) into which fuel gas and combustion-assisting gas are introduce...  
WO/2019/108220A1
There is provided a ceramic matrix composite component (10) having a body (12) comprising a ceramic matrix composite material (14) and a plurality of grooves (24, 25, 26) extending from a top surface (16) of the body (12) and into the bo...  
WO/2019/105540A1
Invention relates to a dual fuel burner assembly (10) comprising a duct part (12) arranged into the burner, a combustion air inlet opening (15) in a first end of the duct part, an outlet (16) at the second end of the duct part (12) and a...  
WO/2019/107369A1
The present invention is provided with a downstream plate (59) that is provided on the downstream side of an upstream plate (58) and includes: an air introduction portion (86) to which cooling air from a cooling air introduction pipe (68...  
WO/2019/097947A1
This combustion cylinder for a gas turbine is provided with an outlet section having a circular fan shape in a cross section. The outlet section comprises an outer wall formed on the outer circumferential boundary of the circular fan sha...  
WO/2019/086986A1
A fuel testing device (100) includes a combustion chamber (140) having an optical access port (142); a visualization system (150) that acquires images of a flame inside the combustion chamber (140), the images being acquired through the ...  
WO/2019/088107A1
Provided are a combustor and a combustion method with which it is possible to inhibit generation of nitrogen oxides. A combustor (10) provided with: a first wall (13A) forming a combustion chamber (12); a fuel injection nozzle (11) which...  
WO/2019/082880A1
A gas turbine combustor (3) is provided with: a nozzle (31A) in which an air ejection passage (F2) that extends along an axis (Ac) and that opens at a distal end thereof and a fuel supply passage (F1) that extends along the axis and that...  
WO/2019/078921A1
A support housing (15) for use in distributing fuel in a gas turbine engine includes a main body (40) defining an inlet aperture, a plurality of outlet apertures, and a substantially planar mounting surface (65). A first fuel channel has...  
WO/2019/067114A1
A scroll (174) for a fuel injector assembly (136) of a gas turbine engine is disclosed. The scroll (174) includes a cylindrical body (220) that has an axial end face (224) and an inner surface (238) defining a bore (240). A passage (254)...  
WO/2019/063908A1
The invention relates to a constant volume combustion chamber (1) for a turbine engine, the chamber (1) comprising an intake port (6), an exhaust port (7), and a first rotary seal (11) arranged opposite the intake and exhaust ports (6, 7...  
WO/2019/058054A1
A method for producing a part from composite material comprises the following steps: - injecting into a fibrous texture (10) a slurry (BC) comprising at least one powder of refractory ceramic particles (CR) suspended in a liquid phase, -...  
WO/2019/058069A1
The invention relates to a method for manufacturing a part using CMC, i.e. a ceramic matrix composite material, as well as such a part made of CMC, the method comprising the following steps: providing (E1) a fibrous reinforcement (10); i...  
WO/2019/057856A1
The invention relates to a method for reacting deliverable fuels, in which fuel is fed to a first reaction region (21, 22, 23, 24) of a reaction body (11) and is reacted in the latter, and in which fuel is fed to a further reaction regio...  
WO/2019/053063A1
A controller (50) for a gas turbine arranged to supply a load L is described. The gas turbine comprises a fuel supply means arranged to supply fuel at a fuel flow rate FF to a combustor. The fuel supply means comprises a first fuel suppl...  
WO/2019/053043A1
A controller (50) for a gas turbine is described. The gas turbine is arranged to supply a load L. The gas turbine comprises a fuel supply means arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the fuel supply means ...  
WO/2019/048387A1
A gas turbine combustor assembly with a trapped vortex feature A combustor assembly (100) of a gas turbine engine (10) having a trapped vortex feature to reduce emissions is presented. The trapped vortex is formed using ammonia injected ...  
WO/2019/043751A1
This fuel injection device is provided with: a pilot fuel injection section having a pilot fuel supply block and a pilot shroud; a main fuel injection section disposed so as to radially externally surround the pilot fuel injection sectio...  
WO/2019/042970A1
A wall (1) of a hot gas component (2), comprises a hot (5) and a cold- gas sided surface (3), one film cooling hole (7) extending from an inlet (8) in the cold-gas sided surface to an outlet (9) in the hot-gas sided surface and comprisin...  
WO/2019/039161A1
A combustor comprising: a plurality of nozzles (2) provided in the circumferential direction; a flame-holding ring extending in the circumferential direction on the inner circumferential side of an outlet part of the plurality of nozzles...  
WO/2019/038496A1
The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber (8) defined by an internal annular wall (12) and an external annular wall provided with air intake openings (32, 34), th...  
WO/2019/028241A1
A combustor assembly (56) for a turbine engine includes a liner panel (64) defining a portion of an inner surface (68) of a combustor chamber (55), liner panel including an end face (70) transverse the inner surface, and at least one dif...  

Matches 1 - 50 out of 12,779