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WO/2023/140180A1 |
A combustor according to at least one embodiment of the present disclosure is a combustor that causes compressed air supplied from a compressor to combust together with fuel. A combustor according to at least one embodiment of the presen...
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WO/2023/138897A1 |
A gas turbine system (1000, 2000, 3000) with a compressor section (10) configured to compress an oxidant flow and to provide a compressed oxidant flow at a combustor section (20). The combustor section (20) is configured to receive the o...
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WO/2023/138906A1 |
A gas turbine system (1000, 2000, 3000) with a compressor section (10) configured to compress an oxidant flow and to provide a compressed oxidant flow at a combustor section (20). The combustor section (20) is configured to receive the o...
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WO/2023/133074A1 |
A method of controlling a fuel blend (26) for a turbine engine (12) is provided. The method includes supplying a first fuel (30) and a second fuel (32) to a mixer (34) and mixing, in the mixer (34), the first and second fuels (30, 32) to...
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WO/2023/127727A1 |
A combustor for gas turbines according to one embodiment of the present disclosure is provided with: an outer wall that surrounds a combustion chamber; a liner that is positioned on the inner side of the outer wall and faces the combusti...
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WO/2023/127691A1 |
This combustor panel comprises an outer surface that faces an inner-side peripheral surface of a shell across a gap, and an inner surface that defines a combustion chamber extending in a flow direction from upstream of the combustor to d...
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WO/2023/127718A1 |
This combustor for gas turbines comprises: a shell that is made from metal; a liner that disposed inside the shell and that is made from a ceramic matrix composite material, said liner having an inner surface which defines a combustion c...
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WO/2023/127728A1 |
A gas turbine combustor according to an aspect of the present disclosure comprises: an outer wall surrounding a combustion chamber; a liner located inside the outer wall and facing the combustion chamber; and a fixture for attaching the ...
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WO/2023/113097A1 |
The present invention relates to a combustion device. A combustion device according to one embodiment of the present invention comprises: a fuel manifold for distributing a fuel, which is flowing in, to one or more fuel inlet ports; a pl...
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WO/2023/065377A1 |
The present invention relates to the field of new concept unsteady combustion. Disclosed are an isolated section shock wave forward propagation suppression structure for an internal combustion wave rotor, and an internal combustion wave ...
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WO/2023/060869A1 |
A low emission nozzle, a low emission dual fuel combustion chamber, and a gas turbine generator set, relating to a generator set. The present invention aims to solve the problem that solutions in the prior art may easily generate high-te...
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WO/2023/058907A1 |
The present invention relates to an injector, a combustor comprising same, and a gas turbine comprising same. The injector comprises: an injector body; and a slit portion formed through the injector body in a reference direction, wherein...
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WO/2023/057722A1 |
The invention relates to a dihydrogen injection device (2) having a longitudinal axis (X), intended to be mounted on an annular base of an annular combustion chamber (4) of a turbomachine, comprising an inner channel (6) for circulating ...
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WO/2023/052195A1 |
The invention relates to an engine, having - a centrifugal compressor (1), - an annular combustion chamber (5), which is arranged downstream of the centrifugal compressor (1) in a longitudinal direction (L) along an engine axis (9), - a ...
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WO/2023/051864A1 |
The invention relates to a method for operating a combustion system (2) of a turbomachine (1) for a flight propulsion system, comprising a compressor (11), a combustion chamber (4), a turbine (15), a heat exchanger (16, 17) arranged down...
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WO/2023/056046A1 |
Exemplary air breathing plasma jet engine and method of operation that can be used in electrically powered aircraft and spacecraft as a hybrid between a turbo jet engine and a ramjet or supersonic sonic ramjet (SCRAMJET) engine. The air ...
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WO/2023/037643A1 |
This ammonia fuel combustion device in which ammonia gas NH3 supplied through an ammonia supply pipe 11 and combustion air Air supplied through an air supply pipe 12 are mixed in a combustion burner 10 and combusted in a furnace 1, where...
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WO/2023/036622A1 |
The invention relates to a burner having a combustion space (1), a multiplicity of swirl channels (2), wherein a swirl channel (2) comprises at least one fuel nozzle (3) for introducing fuel (G) into the respective swirl channel (2), and...
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WO/2023/030467A1 |
Disclosed in the present invention are a combustion chamber having double fuel pipes and a gas turbine. The combustion chamber comprises a flame tube, an igniter, a first swirler, a second swirler, a first fuel pipe, a second fuel pipe, ...
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WO/2023/034365A1 |
A supplemental fuel system includes a fuel mixer. The fuel mixer includes a nozzle and a stem. The nozzle is configured to be positioned within a conduit of an air supply system for a compression-ignition engine. The nozzle has a body de...
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WO/2023/033855A1 |
A combustor (200) includes a combustor wall (202) enclosing a hollow interior (204) for passing a flow of combustion gas from an upstream side to a downstream side. The combustor (200) includes an upstream bluff body (216) enclosed by th...
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WO/2023/027116A1 |
A combustor panel according to the present disclosure comprises: a first panel; a second panel that is disposed to face the first panel, defines a channel for circulating cooling air between the first panel and the second panel, and has ...
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WO/2023/027898A1 |
Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer (300) is disclosed that utilizes an air nozzle (200), in combination with one or more fu...
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WO/2023/025423A1 |
The invention is about a burner component (11) for use in a flow channel (02) of a burner (01) of a gas turbine. A component wall (14) extends from a leading edge (12) to a trailing edge (13) and in a transverse direction cross the flow ...
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WO/2023/013310A1 |
The gas turbine combustor according to at least one embodiment of the present disclosure comprises a burner and fuel piping that supplies fuel to the burner. The fuel piping is connected to a member that separates at least a portion of a...
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WO/2023/014343A1 |
A combustor (120) includes a premixer fuel injector (212) that injects fuel into the combustor and ignites mixture of the fuel and compressed air to produce exhaust gas, a transition duct (210) through which the exhaust gas passes, a sec...
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WO/2023/285298A1 |
The invention relates to a combustion chamber assembly for an engine (103), comprising - a combustion chamber (207) with a combustion chamber head (11), via which air can flow into the combustion chamber (207) along a flow direction (s),...
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WO/2023/273305A1 |
The present invention provides a center-staged combustion chamber based on self-excitation sweep oscillation fuel nozzles, comprising an outer housing internally provided with a cavity, a primary combustion stage coaxially arranged with ...
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WO/2022/270187A1 |
A gas turbine system 100 comprises: an ammonia tank 140 for storing liquid ammonia; an ammonia flow passage 30 which is connected to the ammonia tank 140 to allow the liquid ammonia to flow; a fuel injection nozzle 134 connected to the a...
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WO/2022/255334A1 |
This gas turbine combustor is provided with: a cylinder body that defines a combustion chamber; an air passage for supplying air to the combustion chamber; and a resonator including an opening open to the air passage. The air passage inc...
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WO/2022/249938A1 |
A gas turbine combustor (3) comprising a fuel injection device (13) including: a fuel injection unit (23) having a plurality of fuel injection holes (29) that is provided in a combustion cylinder (11) forming a combustion chamber (9) ins...
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WO/2022/237223A1 |
An afterburner structure based on a new fuel nozzle (152). The fuel nozzle (152) used generates a sweep oscillating jet with a certain frequency at an outlet under the action of a fluid Coanda effect and alternate feedbacks from feedback...
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WO/2022/238011A1 |
A fuel injector (19) comprises a fuel infeed chamber (21) and a centerbody (31) extending along a longitudinal axis from the fuel infeed chamber (21) to a distal end (37) of the centerbody. An outer sleeve (35) surrounds the centerbody a...
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WO/2022/227582A1 |
A combustion chamber structure having a heat exchanger (1), comprising the heat exchanger (1) and a combustion liner (2) embedded into the heat exchanger (1). The heat exchanger (1) comprises a heat exchanger inner wall (11) and a heat e...
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WO/2022/230702A1 |
A combustor structure 1 according to an embodiment of the present invention, this combustor structure 1, comprises: a plurality of combustors 50; a rear liner 60 which guides a combustion gas from the plurality of combustors 50 to the do...
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WO/2022/223915A1 |
A flame-holder device (36) for a turbojet afterburner comprises an annular row of flame-holder arms (38), each having an inner branch (38A) having a free end (50) and another end (52), and two outer branches (38B, 38C) which extend from ...
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WO/2022/223914A1 |
A diffusion cone (33) for the rear part of a jet engine has a base (50) and, on an opposite side, a truncated tip defining an annular trailing edge (58), and comprises a flame-holder ring (70) with a cross section comprising an external ...
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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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