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Matches 1 - 50 out of 12,721

Document Document Title
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...  
WO/2019/027508A1
An acoustic combustor liner for a combustion turbine engine dampens acoustic wave vibrations generated by dynamic pressure variations in the combustion gas. A panel incorporates a meta- structure, also known as a meta-material, acoustic ...  
WO/2019/025094A1
A burner (1) of a turbomachine, particularly a gas turbine engine, comprises at least one burner section (3) having an annular wall (10) surrounding a respective section of a burner interior (6), the annular wall (10) including: - an ann...  
WO/2019/020474A1
A gas turbine engine comprising combustion apparatus (16) defining a volume (26), a compressor (14), a cooling air supply feed (110) from the compressor (14), a Helmholtz resonator (100). The Helmholtz resonator (100) comprises a neck (1...  
WO/2019/020350A1
The invention relates to a burner (1) for an internal combustion engine, said burner comprising multiple mixing tubes (2) which are arranged parallel to one another in concentric rings and have air inlets (3) and, upstream of the air inl...  
WO/2019/017429A1
This combustor is provided with a plurality of main burners disposed at an interval in the circumferential direction. The main burners include first main burners (16A) and second main burners (16B) which separately generate air-fuel mixt...  
WO/2019/015925A1
The invention relates to a method for improving the performance of a gas turbine (1), in which a hub (6) annually surrounding a rotor (2) is machined when the rotor (2) is in the non-stacked state and hot shield elements that are arrange...  
WO/2019/012559A1
The present invention relates to a 3D printed combustion chamber assembly and an additive manufacturing of the combustion chamber assembly. The process involves spreading metal powder layer by layer on a predetermined platform followed b...  
WO/2019/010052A1
A torch igniter (200) includes an auxiliary fuel injector (204); an ignition source (206); and an igniter body (202) carrying the auxiliary fuel injector and the ignition source. The igniter body includes an auxiliary combustion chamber ...  
WO/2019/010056A1
A torch igniter (200) includes an auxiliary fuel injector (204); an ignition source (206); and an igniter body (202) carrying the auxiliary fuel injector and the ignition source. The igniter body (202) includes an auxiliary combustion ch...  
WO/2019/006067A1
Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket (102) may be arranged between an outer wall (104) and an inner wall (106) of the component. A lasing device...  
WO/2019/001996A1
A flat-jet fuel injector for an aircraft turbine engine, comprising a body (112) having a generally elongate shape having a longitudinal axis A, said body comprising a main pipe (118) having a generally elongate shape having a longitudin...  
WO/2018/234698A1
The invention relates to a constant volume combustion system (1) for a turbomachine (10) comprising: a plurality of combustion chambers (100) distributed in a ring about an axis (XX') defining an axial direction (DA), each combustion cha...  
WO/2018/226268A1
A flight vehicle has an engine that includes air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes a bulged region that has at least one dimension, perpendicul...  
WO/2018/217485A1
A refractory ceramic component (10) for a gas turbine engine (100) is employed that is more cost effective than typical components used in the gas turbine engine (100). The refractory ceramic component (10) may include a refractory ceram...  
WO/2018/212761A1
A method for staging premixers in a combustion system for a gas turbine having a compressor section and a turbine section. The method includes providing a plurality of burners each including premixers wherein compressed air from the comp...  
WO/2018/212760A1
A combustion system for a gas turbine. The system includes a cowl having a dome portion and side portions that form an open end. Compressed air from a turbine compressor flows in a first air flow path adjacent the cowl. A liner is locate...  
WO/2018/212001A1
Provided is a gas turbine combustor (3) equipped with a fuel injection device (15) that has a plurality of annular fuel injection parts (25), each having numerous fuel injection ports (25a) formed therein, the gas turbine combustor being...  
WO/2018/203939A2
A trapped vortex combustor for use in a gas turbine engine includes an outer vortex chamber wall and a dome attached to, or formed integrally with, the outer vortex chamber wall. The dome, the outer vortex chamber wall, or both define at...  

Matches 1 - 50 out of 12,721