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WO/2015/171269A1 |
A gas fuel delivery system (330) is disclosed. A gas fuel delivery system includes a gas fuel system (350) and a gas ring (11). The gas fuel delivery system includes an enclosure (370) surrounding the gas fuel system. The enclosure inclu...
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WO/2015/169930A1 |
The present invention is related to a Swirler (50) for a burner (30) of a gas turbine engine (10), comprising a plurality of vanes (54) extending from an outer radius (64) of the swirler (50) to an inner radius (62) of the swirler (50) a...
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WO/2015/165735A1 |
A burner (30) for a combustor (56) of a gas turbine combustor (16) comprises a body (53) having a surface (64) and a burner axis (50), a fuel lance (56), an igniter (58) and a main air flow passage (62) or passages (62). The main air flo...
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WO/2015/166597A1 |
Provided is a gas turbine combustor and the like capable of maintaining flame-holding performance through suppressing the amount of generated NOx while suppressing burning of the area around a pilot nozzle including the pilot nozzle itse...
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WO/2015/165680A1 |
A burner (1) with a longitudinal burner axis (2) and at least a mixing channel (3, 4), formed in an annular manner around the longitudinal burner axis (2), for the mixing of fuel and air. Each mixing channel is bounded radially on the in...
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WO/2015/166902A1 |
The present invention sufficiently ensures the ignition stability and the flame-holding property of an afterburner (25) while suppressing a reduction in the engine efficiency of an aircraft engine (1). A flame holder (45) is disposed dir...
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WO/2015/166017A1 |
A fuel lance (56) for a burner (30) of a combustor (16) of a gas turbine combustor (16), has an axis (79) and comprises a fuel lance body (68) defining a fuel flow passage (70) and a liquid fuel tip (72) attached to the fuel lance body (...
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WO/2015/166921A1 |
The present invention improves the durability of an afterburner (25) and yet suppresses a reduction in the engine efficiency of an aircraft engine (1). A ring-shaped cooling channel (35) through which cooling air (CA) flows is formed bet...
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WO/2015/162795A1 |
Provided is a gas turbine combustor in which a plurality of cooling air passages (27A), through which bled pressure-raised air flows from a downstream side to an upstream side of a combustion gas flow, are disposed in parallel on a wall ...
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WO/2015/160524A1 |
A gas turbine engine combustor basket has nested outer and inner liners that are separated by a gap at their respective distal downstream ends for passage of cooling air between the liners. Radially inwardly projecting platefins formed o...
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WO/2015/158506A1 |
The invention relates to a method for assembling a gas-turbine burner assembly, comprising: a gas-turbine burner (1), which has a tubular combustion chamber (5); a tubular transition channel (6), which conducts combustion gases exiting t...
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WO/2015/158489A1 |
The invention relates to a burner having an air supply and premix duct which is of essentially annular cross-section and through which flow, in operation, air and fuel, and which is formed by an outer jacket and a hub and in which there ...
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WO/2015/156691A1 |
An apparatus and method for servicing a combustion liner in a combustion case of a turbine is provided. The apparatus includes an elongated bar (401) having a handle (403) at one end and a force applying member at an opposing end of the ...
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WO/2015/154902A1 |
The present invention relates to a burner device for a gas turbine. The burner device comprises a burner body (120), wherein the burner body (120) comprises an axial end face (123). The burner body (120) further comprises a first supply ...
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WO/2015/155452A1 |
The fixed vanes (15) of a diffuser (14) are set to an azimuth angle (a) with respect to the injectors (9) of a combustion chamber so that the paths (35) leading from the trailing edges (34) pass through the gaps (38) between injectors (9...
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WO/2015/150088A1 |
The invention relates to a gas-turbine system (2) of a power plant, said system comprising: a compressor (4); an annular combustion chamber (10) having a burner (14); and a turbine (6) coupled to the compressor (4). The gas turbine syste...
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WO/2015/150095A1 |
The invention relates to a silo combustion chamber (1) for a gas turbine (46) which can be coupled to a heat exchanger (54) during operation, comprising a flame tube (12) which is made of an inner wall (2) and a flame tube base (8) and w...
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WO/2015/150114A1 |
The invention relates to a burner (2) having a plurality of pre-mixing chambers (6) each having a fuel nozzle (10) for two fuels, wherein the fuel nozzle (10) has a fuel lance (14) that extends in a flow direction (S), in which fuel lanc...
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WO/2015/151880A1 |
A combustor is provided with a combustion cylinder (12) in which a combustion gas flows through the inner periphery and in which a plurality of through-holes (14) are formed, and a sound attenuator (20) having a space-forming member (21)...
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WO/2015/150098A1 |
The invention relates to a silo combustion chamber (1) for a gas turbine (70), which silo combustion chamber comprises the following: a flame tube (12), which is formed by an inner wall (2) and a flame-tube bottom (8) and which bounds a ...
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WO/2015/151621A1 |
This jet engine is provided with an inlet that takes in air, a combustor (12) that combusts a fuel using air, and a fuel control unit (37) that controls the supply of fuel. The combustor (12) is provided with a fuel supply unit (22) that...
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WO/2015/152760A1 |
A pre-film liquid fuel cartridge includes a main body having a water passage, a liquid fuel passage, a compressed air passage and a pre-film tip disposed at a downstream portion of the pre-film liquid fuel cartridge. The pre-film tip inc...
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WO/2015/150099A1 |
The invention relates to a method for controlling a division of fuel among predetermined burner stages of at least one burner of a machine during steady-state machine operation.
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WO/2015/151620A1 |
This jet engine is provided with an inlet and a combustor. The inlet (11) takes in air. The combustor combusts a fuel using air. The combustor is provided with an injector (20). The injector (20) has an opening portion (31) for injecting...
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WO/2015/150089A1 |
The invention relates to a burner head (1) with a central casing (2), an oil supply line (3) which extends in the axial direction through the central casing (2) and which is fluidically connected to multiple oil outlet openings (9), a co...
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WO/2015/153115A1 |
A system for premixing fuel and air prior to combustion in a gas turbine engine includes a mixing duct, a centerbody fuel injector located along a central axis of the mixing duct, an outer annular swirler located adjacent an upstream end...
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WO/2015/147932A2 |
A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal b...
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WO/2015/147934A1 |
A fuel nozzle includes: an outer body (36) extending parallel to a centerline axis (26), having a generally cylindrical exterior surface (88), forward and aft ends (82, 84), and a plurality of openings (94) through the exterior surface (...
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WO/2015/146375A1 |
This jet engine comprises: an inlet (11) that takes in air; and a combustor (12) that combusts a fuel by using said air. The combustor (12) includes an injector (20), a plurality of flame holders (21, 22), and a disappearing part (31). T...
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WO/2015/146376A1 |
This jet engine comprises an inlet and a combustor. The inlet takes in air. The combustor combusts a fuel by using said air. The combustor (12) includes an injector (20) that is provided with a plurality of openings (31a, 31b) for inject...
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WO/2015/147929A2 |
An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell, a heat shield and an annular body. The body at least partially defines a first aperture through the shell and t...
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WO/2015/147938A2 |
A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radiall...
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WO/2015/147935A1 |
A fuel nozzle apparatus (10) for a gas turbine engine includes: a fuel discharge element (24) having a discharge orifice (50) communicating with a fuel supply connection (104); a static supporting structure (36); and a cantilevered flexi...
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WO/2015/146170A1 |
[Problem] To control the temperature of dehydrogenation to an appropriate range to enable efficient and stable hydrogen generation when exhaust gas of power generation is used as a heat source for the dehydrogenation. [Solution] A hydrog...
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WO/2015/147951A2 |
A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that ...
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WO/2015/148751A1 |
A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone upstream of the secondary fuel stage to ignite working gas. The secondary fuel stage includes a nozzle (18) with dual outlets (2...
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WO/2015/142411A2 |
An article such as a heat shield panel includes a substrate and a multi-layered coating supported on the substrate. The multi-layered coating can include alternating layers of different ceramic material compositions having individual thi...
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WO/2015/141561A1 |
A combustor (10) is provided with: a nozzle (25) having formed therein an air jet section (51) that causes air to be jetted from a nozzle section (25s); a cylindrical member (26) that covers the nozzle (25) from the outer peripheral side...
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WO/2015/136609A1 |
The purpose of the present invention is to provide a combustion burner capable of retaining a flame stabilizing function for a long time without causing erosion of a swirler even if a flame retardant component-containing fuel is used. Th...
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WO/2015/134216A1 |
A fuel injector (310) for a combustor (300) of a gas turbine engine (100) is disclosed. The fuel injector (310) includes a gas outer tube (351), a gas inner tube (340), a liquid tube (370), and a heat shield (390). The gas outer tube (35...
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WO/2015/134010A1 |
A gas turbine engine comprising a compressor exhaust flow static mixing system (10) formed from one or more radially inward extending static mixing arms (12) and one or more radially outward extending static mixing arms (14) that change ...
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WO/2015/132728A1 |
A combustion chamber of a gas turbine assembly comprises: a casing (8), defining a combustion volume (8a) therein; a heat shield (10), which lines the inside of the casing (8) and comprises a plurality of tiles (12, 12a, 12b) of a refrac...
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WO/2015/134009A1 |
A compressor exhaust flow static mixing system (10) formed from one or more radially inward extending static mixing arms (12) and one or more radially outward extending static mixing arms (14) that change the flow pattern of compressor e...
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WO/2015/124840A1 |
The invention relates to an annular turbine engine combustion chamber having an axial direction (X), a radial direction, and an azimuthal direction. Said chamber includes a first annular wall (12) and a second annular wall (14). Each wal...
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WO/2015/126501A2 |
A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner ...
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WO/2015/126511A1 |
A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the comp...
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WO/2015/126587A1 |
A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentr...
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WO/2015/123694A1 |
A method for operating a combustion system includes outputting fuel and oxidant from a fuel and oxidant source onto a perforated flame holder. The method further includes sustaining a combustion reaction of the fuel and oxidant within th...
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WO/2015/121063A1 |
Fuel injection means for a swirler of a burner of a gas turbine engine, swirler for a burner of a gas turbine engine, burner of a gas turbine engine and gas turbine engine. The present invention is related to fuel injection means (50) fo...
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WO/2015/123421A1 |
A distributed sensing system for detecting a flashback condition in a combustor for a gas turbine engine. The distributed sensing system includes one or more strategically positioned fiber optic cables provided upstream of the combustion...
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