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WO/2024/095848A1 |
This control device controls a gas turbine combustor capable of burning fuel gas and air mixed together inside a combustion chamber with a burner. The burner is provided with a first fuel gas injection hole, a second fuel gas injection h...
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WO/2024/095121A1 |
Disclosed herein is a method for controlling instability in a combustion chamber of a gas turbine. This method is done by changing in flow rate of channels of the combustion chamber in the form of reducing a certain amount of flow rate i...
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WO/2024/095847A1 |
This gas turbine combustor can combust a fuel gas and air, which have been mixed in a combustion chamber, using a burner. The burner comprises a first fuel gas spraying hole, a second fuel gas spraying hole, and a first air spraying hole...
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WO/2024/090092A1 |
This combustion system (100) is provided with: an ammonia supply source (1); a cracking device (3) which is connected to the ammonia supply source (1) and decomposes ammonia into hydrogen and nitrogen; a combustor (42) which is connected...
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WO/2024/085093A1 |
This burner comprises a mixing pipe in which a mixing space is formed, and a fuel nozzle disposed in the mixing space. The fuel nozzle comprises a nozzle main body extending in an extension direction of the mixing space, and a projecting...
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WO/2024/084922A1 |
This gas turbine control device controls a gas turbine comprising a combustor capable of generating combustion gas for driving the gas turbine by cofiring a first fuel and a second fuel. When it is determined that the supply of the secon...
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WO/2024/084808A1 |
A gas turbine combustion cylinder according to at least one embodiment of the present disclosure is for a gas turbine and comprises: a combustion cylinder; a plurality of fuel nozzles arranged, on the lateral side of the combustion cylin...
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WO/2024/079656A1 |
A two-stage burner (100) with a two-layer vortex counter current flow comprises a burner body (105) and a flame tube (110) containing an ignition device and an outlet nozzle (120). An air channel (112) with a first swirler (1) is provide...
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WO/2024/075569A1 |
This intermediate shaft cover comprises: a cylindrical inner cover covering an intermediate rotor shaft; an annular outer cover which covers an outer peripheral side of a diffuser space and which is connected to a gas turbine casing; and...
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WO/2024/057775A1 |
An aircraft engine combustor equipped with a cylindrical member for demarcating an internal space which extends along an axis, and a fuel nozzle which is positioned in a manner such that at least a part thereof is positioned inside the i...
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WO/2024/054836A1 |
A dual-fuel turbine engine is a type of turbine engine that can operate using two different fuel sources, such as liquid fuel (e.g., diesel) and natural gas. For liquid fuels, the turbine engine includes a primary line to facilitate engi...
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WO/2024/052611A1 |
The invention relates to a device for injecting a combustible mixture, for a combustion chamber (100) of an aircraft turbine engine turbine, which comprises, about a longitudinal axis (X), a tubular central channel (1), a first annular c...
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WO/2024/049370A1 |
The invention relates to a compact (one-piece) refractory cast iron combustion chamber mold for a circulating fluidized bed boiler for the combustion and/or gasification of biomass, waste, lignite and mixtures thereof, and a method of ob...
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WO/2024/043268A1 |
This gas turbine is provided with a combustor which can switch a fuel to be combusted between an ammonia fuel and a hydrocarbon-based fuel. The combustor has: a cylindrical body which has a cylindrical shape and through which a combustio...
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WO/2024/024197A1 |
A combustion system 10 comprises: a combustion chamber 13c; a cylindrical air chamber 31 which has an injection hole 31a facing the inside of the combustion chamber 13c; a fuel supply path 41 connected to the air chamber 31; and an air s...
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WO/2024/023881A1 |
Provided is a fuel supply system that can identify an internal leak model of a gear pump with high accuracy.　The system comprises: a gear pump; a measurement section including an orifice and a check valve that are connected in parallel...
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WO/2024/018672A1 |
According to the present invention, a gas turbine combustor and a gas turbine comprise: a combustion barrel having a cylindrical shape; a fuel supply unit for supplying a fuel gas into the combustion barrel; a premixed gas supply unit wh...
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WO/2024/014349A1 |
A fuel supply apparatus comprising: a water electrolysis device; a dehumidifier that is provided in a hydrogen line through which hydrogen from the water electrolysis device flows, and includes an adsorbing material for adsorbing water c...
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WO/2024/009587A1 |
Provided are an assembly method and an assembly device capable of identifying, from among a plurality of overlapping regions, an overlapping region that requires adjustment. In this assembly method for assembling a bulkhead (30) to an ou...
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WO/2024/010565A1 |
A micro-turbine core fabricated as a single part using 3D additive manufacturing (AM) to simultaneously form sequential layers of at least two static components from any of the following static components: central bearing support structu...
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WO/2023/243734A1 |
This gas turbine combustor comprises: a shell that surrounds a combustion chamber; a liner that is positioned inward of the shell, and faces the combustion chamber; and a fitting that attaches the liner to the shell. The fitting includes...
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WO/2023/243434A1 |
A hydrogen combustor according to one embodiment of the present invention comprises at least one fuel injector module and a hydrogen supply pipe. The at least one fuel injector module is configured by forming a module from a plurality of...
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WO/2023/238012A1 |
A fuel injector assembly (112) for a combustor of a gas turbine engine includes an annular body defining a hollow interior space (110), first and second openings to the interior space, and a chamber defining a fluid manifold (310). The f...
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WO/2023/235078A1 |
A combustor (202)includes a transition duct (212) having a transition duct liner (224) defining an opening (226) that extends through the transition duct liner, a secondary fuel injector (300) disposed in the opening. The secondary fuel ...
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WO/2023/204847A9 |
An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication w...
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WO/2023/216762A1 |
A deflagration engine having an air intake end not in communication with a fixed combustion chamber, the deflagration engine comprising an air intake duct, a bearing, a shaft, and an aircraft. The deflagration engine further comprises a ...
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WO/2023/219944A1 |
The present disclosure generally relates to fuel burners, for example, for use with photonic crystals as part of thermophotovoltaic power generators or with other thermal power generators. In certain aspects, fuel is supplied into a reac...
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WO/2023/218777A1 |
This cylinder for a combustor that enables combustion of fuel on an inner peripheral side thereof comprises: a plurality of cooling paths that are formed between an inner peripheral surface and an outer peripheral surface and enable circ...
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WO/2023/214294A1 |
A double-skin liner for a combustion chamber of a gas turbine. The double-skin liner includes an inner layer, an outer layer with an expansion gap provided on the outer layer, a gap covering element, a sealing element, a plurality of int...
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WO/2023/214129A1 |
The invention relates to an injection method for an injection device in a combustion chamber of an aircraft turbine engine, the injection device comprising an internal channel (6) surrounded by an external annular channel (8), the channe...
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WO/2023/210226A1 |
This combustor attachment jig is a jig for attaching a combustion cylinder of a combustor to a gas turbine, and comprises a fixed portion capable of being fixed to a combustor insertion hole portion of a casing of the gas turbine, and an...
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WO/2023/204096A1 |
A gas turbine control device of the present disclosure controls a gas turbine in which a combustor is configured in a state where a plurality of fuel supply nozzles for supplying fuel are separated into a first group and a second group. ...
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WO/2023/201132A1 |
A device for electricity generation can include a combustor/recuperator system comprising a recuperator, a combustor, and an emitter; wherein the recuperator comprises an intake for air and fuel, wherein the combustor burns fuels, transf...
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WO/2023/188984A1 |
This combustor comprises a combustor plate which has a downstream end face perpendicular to the combustor axis, a nozzle segment in which a plurality of first nozzles for injecting a premixed gas of air and fuel from the downstream end f...
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WO/2023/189314A1 |
A combustor of the present disclosure comprises: a combustor plate that includes an upstream end surface and a downstream end surface which are orthogonal to a combustor axis; a plurality of mixing tubes which extend across the upstream ...
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WO/2023/188749A1 |
This combustor comprises: a combustor plate that has a mixing tube which extends so as to penetrate the combustor plate upstream end face and downstream end face perpendicular to the combustor axis and into which air is introduced from t...
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WO/2023/180315A2 |
The invention relates to a nozzle assembly for a combustor (103) of an engine (T), comprising at least one nozzle (D) for injecting fuel into a combustion chamber (1030) of the combustor (103), wherein the nozzle (D) comprises a nozzle m...
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WO/2023/181513A1 |
A combustion system (1) comprises: a combustor (12) including a first combustion region (12a) and a second combustion region (12b) continuous with the first combustion region (12a) on a downstream side; a first burner (13) including an i...
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WO/2023/179824A2 |
The present invention relates to a jet burner apparatus (100) for combusting at least one fuel with at least one oxidising agent, wherein the jet burner apparatus (100) comprises a central longitudinal axis (102) and a main flow directio...
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WO/2023/180318A1 |
The proposed solution relates to a nozzle assembly for a combustor (103) of an engine (T), having at least one nozzle (D) for injecting hydrogen into a combustion chamber (1030) of the combustor (103), wherein the nozzle (D) has a nozzle...
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WO/2023/179825A1 |
The present invention relates to a burner device (100) for combusting at least one fuel with at least one oxidising agent, wherein the burner device (100) comprises a central longitudinal axis (102) and a main flow direction (104), which...
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WO/2023/181616A1 |
A device for controlling gas turbine equipment comprises: a combustion load command generator that determines a combustion load command value, which is a parameter having a positive correlation with an inlet temperature, which is the tem...
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WO/2023/180320A1 |
The invention relates to a nozzle assembly for a combustor (103) of an engine (T), comprising at least one nozzle (D) for injecting fuel into a combustion chamber (1030) of the combustor (103), wherein the nozzle (D) has a nozzle main bo...
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WO/2023/176570A1 |
A gas turbine combustor according to at least one embodiment of the present disclosure comprises a plurality of narrowing parts that protrude toward the inside of a combustion cylinder. The center axis of the combustion cylinder includes...
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WO/2023/173792A1 |
An oblique spraying non-premix annular combustion chamber ignition mechanism research device, comprising a gas distribution chamber (15), an annular combustion chamber (16) and an atomization jet assembly. The gas distribution chamber (1...
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WO/2023/171681A1 |
A rotating detonation engine comprising: an outer cylinder that extends in an axial direction; a base that is connected to the outer cylinder, and comprises a plurality of fuel injection ports positioned in a circular ring shape and inje...
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WO/2023/172178A1 |
A method for the combustion of a fuel gas in a combustor unit (114a-c), wherein the combustor unit (114a-c) comprises a first swirler (202; 302; 402); a second swirler (204; 304; 404) downstream of the first swirler (202; 302; 402); and ...
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WO/2023/171430A1 |
This assembly comprises a wall body in which is formed a through-hole passing through in a thickness direction, and a component fixed to one surface of the wall body so as to cover the through-hole, a welded part welded so as to fix the ...
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WO/2023/166126A1 |
The invention relates to a supply device (1), in particular for use in a gas turbine, for supplying an oxidizing agent (38) and fuel (27) to a combustion chamber (3) without a swirling flow, comprising a supply nozzle (10) with a nozzle ...
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WO/2023/162375A1 |
A combustion device comprises a plurality of burners to which ammonia and second fuel are supplied, and a control device. The control device is configured such that in a first load region S1 including zero load, the control device suppli...
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