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WO/2020/092896A1 |
A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of ...
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WO/2020/089873A1 |
A double swirl burner including an annular air nozzle, an annular fuel nozzle coaxially disposed within the annular air nozzle, and a central air nozzle coaxially disposed within the annular fuel nozzle. An annular air nozzle may include...
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WO/2020/083934A1 |
The present invention relates to a fluid energy machine (1), for example a gas turbine or similar combustion engine for the production of energy or for use as a propulsion unit, comprising a combustion chamber (2) with a combustion space...
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WO/2020/076975A1 |
Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and ...
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WO/2020/074224A1 |
The invention relates to a burner (1) for a gas turbine with a supply zone (2) for supplying fuel and air and a subsequent mixing zone (3) for premixing fuel and air, the mixing zone (3) having an upstream end (4) and a downstream end (5...
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WO/2020/071399A1 |
An annular gas turbine combustor for airplanes comprising a plurality of resonators that have resonance chambers and that are disposed in a fuel injection device installation space side-by-side with a fuel injection device in the radial ...
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WO/2020/069811A1 |
The invention relates to a component for a combustion chamber of a gas turbine, which component has a multi-layer structure in the form of ceramic films and/or paper made of pre-ceramic material, the inner and outer structure of the comp...
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WO/2020/068650A1 |
The subject matter of this specification can be embodied in, among other things, a fuel delivery component, including a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defi...
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WO/2020/067231A1 |
A combustor equipped with a fuel nozzle for injecting fuel, a combustion cylinder surrounding a combustion space for combusting the fuel and having an internal flow passage having an outlet communicating with the combustion space, and a ...
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WO/2020/068644A1 |
The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the...
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WO/2020/058617A1 |
The invention relates to a method for determining the flow rate of combustible fluid injected inside a combustion chamber (120) of a turbine (100): determining the cross section of the orifice of said at least one injector (112, 113, 114...
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WO/2020/050854A1 |
An angular cooling arrangement to provide increased mechanical life is presented. The cooling arrangement includes a cooling channel disposed in a combustor liner (28) adapted to provide a region of blocking flow within a combustor exit/...
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WO/2020/048880A1 |
The invention relates to burner (1) with a burner head comprising a main mixing tube (2) for premixing combustion air and fuel, wherein the main mixing tube (2) is provided with a pilot burner system (3) in its downstream part, wherein t...
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WO/2020/048856A1 |
Burner (01) for a combustor of a gas turbine, the burner (01) comprising in fluid flow sequence a swirler section (02) and a mixing section (12) and an outlet section (32) generally arranged around a burner axis (10). At the swirler sect...
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WO/2020/049861A1 |
Provided is a liquid fuel injector that allows the film thickness of a liquid fuel to be injected to be made smaller. In the interior of this liquid fuel injector, a ring-shaped fuel channel extending in the axial direction is provided, ...
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WO/2020/046379A1 |
A cooling channel arrangement for a region of a gas turbine engine is provided. The arrangement includes a cooling channel 26 having cooling sections 34, 36, 38 adapted for use in a component 24 with various component regions 28, 30, 32,...
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WO/2020/046381A1 |
A method for manufacturing a heat transfer design for progressive htc cooling channel arrangements for a region of a gas turbine engine is provided. The 5 method includes generating a non-transitory computer-readable three-dimensional (3...
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WO/2020/046384A1 |
A method of manufacturing a turbine engine transition duct exit frame is described. First, a transition duct exit frame is obtained. Second, a first cooling channel (28) is formed within an end region of the exit frame. Third, a second c...
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WO/2020/025234A1 |
The invention relates to a combustion chamber (18) of a turbine, particularly a thermodynamic cycle turbine with recuperator, for generating power and particularly electrical power, comprising a casing (112) with a means (152) for inject...
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WO/2020/025233A1 |
The invention relates to a combustion chamber (18) of a gas turbine, particularly a gas turbine with a thermodynamic cycle with a regenerator, for the production of energy, in particular electrical energy, comprising a housing (112) and ...
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WO/2020/016533A1 |
The invention concerns an assembly for a turbomachine, including - a combustion chamber (1) comprising, at its downstream end, a radially-extending downstream flange (6), - a guide vane (2) arranged downstream of the combustion chamber (...
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WO/2020/012112A1 |
Constant-volume combustion system (1) for a turbomachine, comprising a plurality of combustion chambers (2) distributed in a ring about a main axis (Θ), said combustion chambers (2) comprising intake ports (21) and exhaust ports (22), t...
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WO/2020/011311A1 |
In order to provide a method for operating a gas turbine apparatus, which method permits a simple and/or compact configuration and energy-efficient use of the gas turbine apparatus for raw gas cleaning, it is proposed that the method for...
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WO/2020/009786A1 |
A center body assembly (700) for a lean direct injection fuel injector (600) is disclosed. The center body assembly defines a primary liquid passage (721), a liquid gallery (880), a liquid main first passage (875), a liquid main second p...
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WO/2020/003708A1 |
The present invention provides a method for operating a combined power generation facility that can shorten the start-up time of the combined power generation facility (shorten the time to reach the rated load) and enables high-efficienc...
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WO/2020/002858A1 |
The invention relates to a device for guiding an element in an opening in a wall of a combustion chamber. Between the welds or solders (800) and the movement path (600a) of the rim of the ring (500), an intermediate space (881) is reserv...
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WO/2020/001606A1 |
A low pollution combustor and combustion control method therefor. The low pollution combustor comprises a combustor dome (12), the combustor dome (12) comprises a main combustion stage (14) and a pre-combustion stage (15), and the main c...
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WO/2019/240116A1 |
This diffusing combustion type fuel nozzle of a gas turbine is provided with: a nozzle body; a plurality of nozzle holes which extend along the axial direction of the nozzle body and are arranged along the circumferential direction of th...
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WO/2019/230165A1 |
Provided is an airflow atomization-type liquid fuel injector by which necessary atomization can be achieved with air at a low flow rate. A liquid fuel injector (100) is provided with: a cylindrical center body (110) having the center axi...
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WO/2019/224484A1 |
The invention relates to a bottom wall (118) of a gas turbine engine combustion chamber. This bottom wall comprises openings (119) for mounting systems for feeding combustion air and holes (128) for passing cooling air, between at least ...
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WO/2019/222702A1 |
A propulsion system includes a source of compressed fluid, at least one thruster in fluid communication with the source, at least one turbine in fluid communication with the source and coupled to a propeller, and an apparatus for selecti...
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WO/2019/222334A1 |
A combustor for a gas turbine engine having a compressor upstream of the combustor and a turbine downstream of the combustor. The combustor also includes a combustor chamber, an oxy-fuel pilot burner (104) centrally positioned at an end ...
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WO/2019/211082A1 |
The invention relates to a component wall (10) of a hot gas component for a gas turbine, which in a double-walled design, comprises an outer wall (12) which is hotter during operation and an inner wall (14) which is cooler during operati...
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WO/2019/207230A1 |
An injection system (19) for a turbine engine annular combustion chamber, comprising - support and centring means (19a) for a fuel injector head, these means comprising a frustoconical surface (30) connected at its downstream end of smal...
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WO/2019/204389A1 |
A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection ("EFI") system that further includes one or more electrically controlled fuel injectors that can be s...
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WO/2019/201577A1 |
The invention relates to a burner assembly (7) comprising a combustion chamber (8) and multiple burners (1) arranged on a circle around the combustion chamber (8), wherein the burners (1) comprise vortex-inducing internal fittings (2), b...
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WO/2019/202917A1 |
[Problem] To observe a predictor of or the occurrence of unstable operation of a turbo machine. [Solution] An observation device 1 having: a detection unit 10 that is arranged in a turbo machine 2 and has one or more sensors 11 and 12 th...
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WO/2019/194817A1 |
A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rota...
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WO/2019/185246A1 |
The invention relates to a moulded part made oxide composite fibre ceramic, referred to below as a "CMC moulded part", such as can be used, for example, in a turbine component, in a burner and/or in an exhaust gas system, in particular o...
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WO/2019/188484A1 |
This fuel supply device is provided with a first supply pipe (2f), a first on-off valve (V1), a second on-off valve (V1, V2), a second supply pipe (2d), a connecting pipe (2h), a third on-off valve (V3), and a leak check measuring device...
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WO/2019/188409A1 |
A combustion device (C) that uses combustion air to burn a fuel inside a combustion chamber (N). The combustion device (C) is equipped with a reducing agent injection device that has injection openings (2n) and that injects a prescribed ...
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WO/2019/185232A1 |
The invention relates to a fuel feed device (1) comprising: a fuel nozzle (2) having a fuel feed channel (3) extending in an axial direction and a plurality of fuel outlet channels (4), which branch off from said fuel feed channel, exten...
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WO/2019/188012A1 |
A combustion device (C) according to the present disclosure causes fuel to burn in a combustion chamber (N) using combustion air, and is provided with a reducing agent injecting portion (2e) which injects a reducing agent toward a flame ...
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WO/2019/187782A1 |
A fuel gas cooling system and a gas turbine plant are provided with: a gas cooler (39) which performs cooling by causing cooling water (CW) to come into contact with compressed fuel gas (FC) serving as a fuel gas; a cooling water dischar...
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WO/2019/187559A1 |
Provided is a combustor wherein flashback can be sufficiently suppressed while reducing NOx. This combustor comprises: a casing 20 having in the interior thereof an air chamber 121 filled with air; mixed flow path formation members 131, ...
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WO/2019/185736A1 |
A device for producing pressure waves of high amplitude, in particular for cleaning boilers, has a pressure-tight vessel (21, 40) comprising a burning chamber (121) introduced therein, which can be filled via feed lines with a flowable m...
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WO/2019/181188A1 |
This fuel nozzle for a gas turbine comprises: a nozzle body; a fuel injection opening formed in the nozzle body so as to have, on a one-end side, an injection port that opens in the outer surface of the nozzle body; and a fuel channel pr...
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WO/2019/181183A1 |
This fuel nozzle for a gas turbine, which injects fuel, is provided with: a purge gas line which extends in the axial direction of the fuel nozzle and which discharges purge gas from the downstream end, in the axial direction, of the pur...
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WO/2019/179691A1 |
The invention relates to a burner (1) with a control unit (11), a combustion chamber (10), a pressure sensor and fuel stages (2, 3, 5, 6, 8) which are arranged to supply fuel with a respective mass flow to the combustion chamber (10), wh...
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WO/2019/181877A1 |
This combustor (22) is provided with: a fuel supply section (35) defining on a radially inner side of an axis line (A) an inner periphery side space (34a) into which inert gas (E) is introduced and which supplies the inert gas (E) to a c...
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