| Document |
Document Title |
|
WO/2020/123093A1 |
A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel delivery system for receiving and distributing fuel and an injector body. The injector body includes a primary fuel gallery, a...
|
|
WO/2020/120828A1 |
A method for burning fuel is disclosed. The method comprises supplying cold non- preheated combustion air and dust fuel into a combustion chamber of a boiler through a burner (10) for producing a flame, the combustion air comprising prim...
|
|
WO/2020/116113A1 |
This gas turbine combustor is provided with: a flange part which is attached to a casing; an annular extension part which extends from the flange part along the axial direction of the combustor; a pipe which has a first end connected to ...
|
|
WO/2020/111114A1 |
This power generation apparatus comprises: a combustor that burns ammonia and air and discharges a mixed gas after the burning; a supplier that includes a compressor that compresses the air and the mixed gas after the burning, supplies t...
|
|
WO/2020/109089A1 |
The present invention relates to a fuel injector (1) comprising a fuel channel (2), a nozzle (3) and cooling means with circulation of a fluid extending along the fuel channel. The cooling means comprise a first passage (6) around the fu...
|
|
WO/2020/099867A1 |
The present disclosure is directed to a system comprising a recuperated gas turbine engine with a catalytic combustor, and methods of operating the same, the catalytic combustor comprising: (a) an upstream section comprising an electrica...
|
|
WO/2020/102705A1 |
A swirl preburner having a first swirl core defining a first swirl chamber having a first swirl chamber first end and a first swirl chamber second end. The swirl preburner further includes a second swirl core defining a second swirl cham...
|
|
WO/2020/095857A1 |
A combustor component according to at least one embodiment of the present invention is provided with: a cylindrical body that has a combustion chamber on the inside, and that has a welding part in which a plurality of through holes are f...
|
|
WO/2020/092916A1 |
A heat transfer mechanism is provided comprising a plurality of turbulators located along a surface of a body, such as a combustion liner. The turbulators have a first side with a first ramp angle, a second side with a second ramp angle,...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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/...
|
|
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...
|
|
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...
|
|
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, ...
|
|
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,...
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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 (...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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 ...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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 ...
|
