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WO/2022/223916A1 |
The invention relates to a fuel injection device (34) for a turbojet engine afterburner, comprising a base (80), a fuel tube (40) provided with fuel ejection ports (44), an air tube (50) provided with cooling air passage ports (54), and ...
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WO/2022/214384A1 |
A combustor (100) for a gas turbine comprising a combustion chamber (102) having an inlet (104). The combustion chamber inlet (104) is defined by a burner (30). The burner comprises a pilot burner section (200) centred on the centre axis...
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WO/2022/209993A1 |
A combustor according to the present disclosure includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which tube plate is formed an air hole passing through the...
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WO/2022/202516A1 |
A combustor for a gas turbine according to one embodiment of the present invention includes an acoustic device that is located on the downstream side of a combustion pipe and has: a first region that lies in at least any one of a pair of...
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WO/2022/202196A1 |
This combustion device 10 comprises: a liner 13b that has an opening 13f provided to an end section thereof and a combustion chamber 13c formed therein; an air flow path 23 communicating with the opening 13f in the liner 13b; an ammonia ...
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WO/2022/202103A1 |
A combustion device 10 comprises: a combustion chamber 13c; and a plurality of flow paths 30 each having a hydrogen flow path 31 that has a hydrogen injection port 31a facing into the combustion chamber 13c, a first air flow path 32 that...
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WO/2022/202104A1 |
A combustion device 10 comprises: a combustion chamber; a plurality of hydrogen injection holes 31 that face into the combustion chamber and are spaced apart in the circumferential direction of the combustion chamber; an annular first ai...
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WO/2022/196552A1 |
This abnormality detection system for a gas turbine combustor comprises: a sensor for detecting whether or not a spark plug, which is provided so as to be movable between an inserted position at which the spark plug is in the combustion ...
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WO/2022/193067A1 |
A combustion chamber for suppressing combustion oscillation, and a combustor comprising the combustion chamber. The combustion chamber comprises: a pre-combustion stage, a main combustion stage, a combustion chamber body, and an anti-osc...
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WO/2022/190689A1 |
Provided is a seal member which forms a combustion gas flow path of a gas turbine, wherein: the seal member includes a first main body part having therein a cooling path; the first main body part comprises a first end section which forms...
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WO/2022/191878A1 |
A dual mode ramjet or scramjet engine (10) used in the propulsion of an aircraft includes an inlet (14) configured to receive and compress air, a combustion chamber (16) connected to the inlet and configured to mix the compressed air wit...
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WO/2022/181694A1 |
A cylinder for combustion (20) comprises a barrel (21) that forms a cylindrical shape, and an air supply pipe (40). An insertion opening (25) and a plurality of cooling flow paths (30) are formed in the barrel (21). A part of the air sup...
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WO/2022/182853A1 |
A hydrogen injection arrangement (1) includes an injector assembly that includes an outer conduit (5) configured to feed a flow of a mixture of air and fuel( 3a) to a combustion chamber (2a) of a combustor. At least a swirler (3) can be ...
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WO/2022/182324A1 |
A premixer injector (300) in a gas turbine engine includes an inlet end (302), an outlet end (304), a first wall (306) and a second wall (308) between the inlet end (302) and the outlet end (304). The first wall (306) has a plurality of ...
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WO/2022/174986A1 |
The invention is about a transition (01) of a combustion section (06) of a gas turbine (04) comprising a bulge (23) and an exit frame (33) and in-between a channel wall (02), wherein a flow channel (03) crosses the transition from an ups...
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WO/2022/175621A1 |
The invention relates to a turbomachine subassembly comprising a first component (10) forming a portion of a wall of a combustion chamber of the turbomachine and a second component (12) forming a connecting member connecting the first co...
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WO/2022/176302A1 |
This premixed combustion burner comprises: an outer tube that has an inlet opening on the first side in the axial direction in which the axis extends and an outlet opening on the second side in the axial direction; an inner tube that is ...
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WO/2022/173040A1 |
This gas turbine plant is provided with a gas turbine and a fuel supply facility. The fuel supply facility is provided with: a liquid ammonia line; a warm water line through which warm water can flow; a vaporizer which can perform the he...
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WO/2022/171451A1 |
The present invention relates to a combustion system with a tubular combustion chamber (5) and an annular counter-flow heat exchanger (4) around the combustion chamber (5).
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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 ...
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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)...
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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 ...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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)...
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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).
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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...
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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)...
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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...
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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...
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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 (...
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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...
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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...
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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)...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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 ...
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