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Matches 1 - 50 out of 9,472

Document Document Title
WO/2022/156925A1
The invention is about a combustion section (01) of a gas turbine (02) comprising an annular combustion chamber (07), and a burner arrangement (08) upstream of the combustion chamber (07), and an annular compressor diffusor (15), and an ...  
WO/2022/152621A1
A system (S) for supplying fuel (C) to the combustion chamber (5) in an aircraft turbine engine (6), comprising injectors (1) comprising a first pilot stage (10), a second pilot stage (16) and a main stage (13), the pilot stages (10, 16)...  
WO/2022/154693A1
The invention relates to devices for the combustion of gaseous fuel, and more particularly to vortex burners. The technical result consists in simplifying a burner structure which provides for a low temperature of the inner surface of a ...  
WO/2022/152622A1
A microtube cluster burner (1) comprises a multitude of ducts (41) extending through fluid plenums (31, 32, 33). Discharge means (51, 52) fluidly connect the plenums to the ducts. At least one of the ducts (41) is provided with at least ...  
WO/2022/149540A1
A gas turbine combustor according to at least one embodiment of the present invention comprises: a low combustible fuel flow adjuster for independently adjusting the amounts of low combustible fuel to be supplied to a first fuel injector...  
WO/2022/144206A1
A double wall (2) for an aircraft gas turbine combustion chamber (1) comprising an internal wall (21) which is configured to be in contact with the combustion reaction, and an external wall (22) which is at a distance from the internal w...  
WO/2022/128959A1
A method of operating a combustion system (16) for a gas turbine (10), the combustor system (16) comprises a main fuel supply (72, 73), a pilot fuel supply (74), a combustion chamber (38). The method comprises the steps supplying a first...  
WO/2022/117465A1
A method of controlling a combustor of a gas turbine engine, the method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fu...  
WO/2022/117464A1
A method of controlling a combustor of a gas turbine engine is disclosed. The method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split in...  
WO/2022/112726A1
The present invention relates to a combustion module (1) for a turbomachine (10), comprising: - an annular casing (3) extending about a longitudinal axis (X); - an annular combustion chamber (2) located inside the casing (3) and comprisi...  
WO/2022/106494A2
The present disclosure relates to a vortex chamber comprising a cavity elongating along a central axis and a swirl generator. The swirl generator comprises a plurality of swirl channels configured for introducing a gas flow into the cavi...  
WO/2022/101608A1
System comprising a gas turbine engine fuel injection apparatus (11) arranged to deliver to a combustion chamber (9) of a gas turbine engine a first injection fluid comprising a first fuel and a second injection fluid comprising a second...  
WO/2022/099955A1
The present invention provides a method for keeping combustion of a gas turbine stable in a dynamic process, a computer readable medium, and a gas turbine control system. The method comprises: compensating for a fuel control valve stroke...  
WO/2022/100089A1
A multi-fuel combined cooling, heating and power system, comprising a multi-fuel micro gas turbine (1); the multi-fuel micro gas turbine (1) comprises a heat regenerator (101) and a combustion chamber (105); hollow evaporation pipes (14)...  
WO/2022/096210A1
The invention relates to a resonator ring (12) for a combustor basket that has orifices (24), insertion plates (27) being connected to the ring (12) inside the orifice (24).  
WO/2022/089822A1
Disclosed is a combustion device (100) for an electricity production or energy cogeneration apparatus, characterised in that: the combustion tube (5) is closed by a bottom (12) at its other end, referred to as the back end, the bottom (1...  
WO/2022/089804A1
The invention is about a burner supply tube (01) and a burner arrangement comprising such a burner supply tube (01). This (01) comprises a tube wall (05) extending having a tube diameter (07) and at least one integrated fuel channel (11)...  
WO/2022/087279A1
An exhaust gas aftertreatment system includes a housing assembly, a first catalyst member, and a second catalyst member. The housing assembly includes an upstream housing, a decomposition housing, a distributing housing, and a catalyst m...  
WO/2022/079523A1
An adjustable injector system (100) for adjusting a radial distribution of a mixed fuel (117) includes an adjustable injector (110) configured to receive first and second non-carbon fuels (112, 114) and configured to adjust the radial di...  
WO/2022/079368A1
An injector for simultaneously injecting at least two fluids into a chamber comprises at least one injection element (10) which is capable of receiving the fluids separately via an axial conduit (1) and via at least one lateral channel (...  
WO/2022/081569A1
An electrically decoupled jet engine. The electrically decoupled jet engine includes a combustion chamber which creates a toroidal flow of air and a rotational electric motor which drives a fuel supply into the combustion chamber. The to...  
WO/2022/075299A1
A gas turbine combustor according to at least one embodiment comprises: a tubular member; a plurality of premixing tubes that are arranged in the circumferential direction on the inner side of the tubular member and each form an outlet p...  
WO/2022/067359A1
A method and a device for uniform recursive sequential combustion of fuel and oxidant within a thermal system with continuous flow, in particular a combustion chamber (1) of an engine or of a gas turbine, • -wherein fresh air (oxidant)...  
WO/2022/048809A1
The invention relates to a seal (11) for use in a heat shield element (01). The seal (11) extends along a longitudinal direction and has a groove face (13) on a hot side (03) and a bearing face (14) on a cold side (04) and mutually oppos...  
WO/2022/050259A1
A gas turbine combustor porous plate according to at least one embodiment of the present invention is installed between the inner and outer cylinders of a gas turbine combustor and is fixedly disposed on the outer periphery of the inner ...  
WO/2022/043079A1
A combustor (36) for a gas turbine, the combustor (36) comprising a combustor axis (44) about which is arranged in flow sequence a radial swirler (40), a pre-chamber (42) and a combustion chamber (38). The radial swirler (40) comprises a...  
WO/2022/036996A1
A rotor supercharged gas turbine. In addition to a first row of combustion chambers (45) provided on a rotor (41), a second row and a third row of combustion chambers (45', 45'') are further provided after the first row of combustion cha...  
WO/2022/035460A1
A gas turbine engine includes a compressor section, a combustor section, a turbine section, a hot gas path and a layered component (600) including a substrate (502) and a thermal barrier coating (TBC) (602) having: a single layer of 6-15...  
WO/2022/018119A1
The invention relates to a nozzle cluster comprising a plurality of pairs each made up of a first (1) and a second gas outlet opening (3). In each pair the second gas outlet opening (3) runs at least partially around the first gas outlet...  
WO/2022/015321A1
A premixer injector assembly in a gas turbine engine includes at least one premixer injector. The premixer injector includes a fuel tube having a fuel feed passage enclosed by an outer surface, a plurality of fins coupled to the fuel tub...  
WO/2022/007373A1
Disclosed is a rotor (41) supercharged gas turbine, wherein a rotor (41) having several combustion chambers (45) is provided between a gas compressor (9) and a turbine (25), and the rotor (41) is mounted in a rotor housing (28); and the ...  
WO/2022/008820A1
Annular combustion chamber (1) for an aircraft turbomachine (3), said chamber having two coaxial annular walls, an inner annular wall (11) and an outer annular wall (12), respectively, which are connected upstream by an annular bottom wa...  
WO/2022/003540A1
The present disclosure provides methods for controlling volumetric flows of streams into a combustor (10a), and particularly in a combustor utilized in a power production method. A controller (210) can be used to receive a variety of inp...  
WO/2021/261431A1
A fuel injection device having a main body section extending in an axial direction, wherein the main body section includes an axial flow passage formed so as to extend in the axial direction, a radial flow passage formed such that one en...  
WO/2021/255364A1
The invention proposes that bridges (9) extending adjacent to each other integrally link a radially inner wall (5) and a radially outer wall (3) of a combustion chamber of a gas turbine engine towards a free end (5a) of the radially inne...  
WO/2021/251325A1
Provided is a gas-turbine premixing tube structure that, in the generation of a mixed gas combining a combustion gas with air, generates a mixed gas that is uniformly and sufficiently diluted. Air holes 1a1, 1a2, 1a3, 1a4 are formed in...  
WO/2021/243949A1
A gas turbine power generation device using viscous force to convert pulse detonation gas energy, comprising an air intake channel (1) and a compressor (2); the air intake channel (1) is located at the front end of the gas turbine, the c...  
WO/2021/243832A1
A pulse detonation combustion chamber (12) having a detonation gas energy distribution smooth structure. The pulse detonation combustion chamber comprises a combustion chamber air inlet channel (1), the pulse detonation combustion chambe...  
WO/2021/242229A1
A combustor includes a pressure-containing housing (22) and a one- piece body (24) disposed along an axis. The one-piece body has an exhaust manifold section (40) and a liner section (42). The exhaust manifold section defines a flow path...  
WO/2021/228447A1
The invention relates to a pilot cone (1) for use in a burner arrangement (2) having a pilot burner (3). The pilot cone (1) comprises: a casing (4) which widens downstream along a burner axis and has a plurality of cooling air passages (...  
WO/2021/224681A1
An improved power generation system and methods of its operation are provided, wherein the system combines: (i) a wave reformer, (ii) an optional second wave rotor, and (iii) a gas turbine in a flexible range of novel designs. Such a hyb...  
WO/2021/217792A1
Disclosed in the present invention is a combustion assembly structure of a turbojet engine. A guide device and a front cover are respectively provided at two ends of a casing having a cavity structure in the middle, a shaft sleeve coaxia...  
WO/2021/215458A1
A cluster burner provided with a plurality of burners for mixing fuel and air, wherein each of the plurality of burners includes a fuel nozzle for injecting fuel, a mixing flow passage to which the fuel and air are supplied, and a suppor...  
WO/2021/215023A1
This burner assembly comprises a plurality of burners for mixing a fuel and air, wherein: the plurality of burners each include at least one fuel nozzle for jetting the fuel, and a mixing flow passage into which the fuel jetted from the ...  
WO/2021/215461A1
This burner assembly comprises a plurality of burners for mixing a fuel and air, wherein: the plurality of burners each include at least one fuel nozzle for jetting the fuel, and a mixing flow passage into which the fuel jetted from the ...  
WO/2021/209711A1
The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, th...  
WO/2021/203583A1
A dry low-nitrogen staged combustion system based on isolating N 2 from the diffusion combustion flame surface, comprising a combustion chamber (19) as well as a purge gas passage (18), a diffusion combustion fuel passage (14), a primary...  
WO/2021/198598A1
The invention relates to a method for the additive manufacturing of a wall (10) for a turbine engine, the wall (10) comprising a first cooling aperture (40). The manufacturing method comprises the additive manufacturing of the wall (10) ...  
WO/2021/201093A1
This gas turbine combustor comprises a first fuel nozzle group and a second fuel nozzle group including fuel nozzles capable of supplying fuel. The first fuel nozzle group and the second fuel nozzle group have fuel supply systems that ca...  
WO/2021/197654A1
The invention relates to a burner component (01) of a burner. The burner has a flow channel, in which combustion air flows in a flow direction (05) from upstream to downstream. The burner component (01) comprises: - a wall portion (03), ...  

Matches 1 - 50 out of 9,472