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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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WO/2023/158807A1 |
Gas turbine combustor assembly (100) comprising a primary combustion chamber (106) in fluid communication with a primary fuel injector and a primary air inlet, and an igniter (200) carried by the primary combustion chamber an including a...
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WO/2023/153042A1 |
An injection nozzle 100 comprises: an inner wall 101 that has a cylindrical shape; a first outer wall 102 that has a cylindrical shape and is formed as integrated with the inner wall 101 via a connection portion 107; a fuel passage 108 t...
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WO/2023/147943A1 |
The fuel nozzle (17) comprises a stem (19) and a first fuel feed channel (61) extending inside the stem (19) from an inlet end (61A) positioned at a proximal end (19A) of the stem (19) to a first fuel inlet plenum (25). The fuel nozzle f...
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WO/2023/145627A1 |
A gas turbine combustor according to at least one embodiment of the present disclosure is provided with: a combustion cylinder having therein a combustion chamber and having formed therein a plurality of through-holes that open to the co...
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WO/2023/145218A1 |
This combustion device 10 comprises a burner plate 14a that faces a combustion chamber, a plurality of injection hole groups 30 that are each formed as a ring in the burner plate 14a, and a ring-shaped slit 50 that is formed between the ...
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WO/2023/143663A1 |
The invention relates to a fuel treatment device (10) for a combustion system of a turbomachine, having a vapour line (13) conducting water vapour (W), a fuel line (14) and a fuel supply device (15) by means of which fuel (B) can be supp...
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WO/2023/140183A1 |
At least one embodiment of the present disclosure relates to a control method for a gas turbine combustor comprising an air-hole plate having a plurality of air holes formed therein, and a plurality of fuel nozzles corresponding to respe...
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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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