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WO/2016/129588A1 |
Provided is a coated member which is provided with a heat shielding coating layer that exhibits excellent characteristics in a high temperature environment in which water vapor is present. A coated member (100) which is provided with a h...
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WO/2016/124348A1 |
The invention relates to an annular combustion chamber (1) comprising an outer shell (2), a number of heat shield elements (3) which are releasably secured to the inside (4) of the outer shell (2), and an annular duct, referred to as a b...
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WO/2016/126980A1 |
A system includes a turbine combustor having a first volume (76) configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber (60) and a second volume (92) configured to receive a first flow of an...
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WO/2016/126986A2 |
A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chambe...
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WO/2016/126985A1 |
A system includes a turbine combustor having a first volume (76) configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume (92) configured to rec...
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WO/2016/124472A1 |
The invention relates to a power co-generation apparatus including a gas microturbine supplied by a "vortex" combustion chamber (1) for carrying out a "flameless" combustion mode and having at least one recovery device / heat exchanger (...
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WO/2016/121694A1 |
In a transition piece (20) are formed a plurality of cooling passages (35) extending in an axial direction (Da) and aligned in a circumferential direction (Dc) and the axial direction (Da). One or more downstream-side passages (43, 44) a...
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WO/2016/120551A1 |
The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: a plurality of combustion chambers (12) distributed angularly i...
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WO/2016/120555A1 |
The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers (12A, 12B) arranged about an a...
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WO/2016/122521A1 |
A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches int...
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WO/2016/122529A1 |
A fuel injector for injecting fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) and a second fuel supply channel (20) may be coaxially arranged in a fuel delivery structure (12). A fir...
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WO/2016/116700A1 |
The invention relates to an assembly comprising an injection system (30) and an injector (20) for an aircraft turbomachine combustion chamber (8), the system (30) comprising an aerodynamic bowl (40) comprising a first end widening toward...
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WO/2016/116176A1 |
A combustion chamber (10) for a gas turbine engine (1) comprises : an inner wall (22) delimiting an inner volume (V) of the combustion chamber (10), through which combustion gas flow from a burner (2) to a gas turbine (3) of the gas turb...
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WO/2016/118133A1 |
A combustor inlet mixing system formed from a plurality of circumferentially spaced swirler vanes (38) extending radially outward from a nozzle hub. Each of the swirler vanes (38) may have a length (62) that extends downstream along at l...
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WO/2016/116686A1 |
The invention relates to an arrangement (200) for an aircraft turbine engine combustion chamber, comprising an injection system and a fuel injector, the injection system comprising a spray nozzle guide (26), the inner surface (40) of whi...
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WO/2016/115152A1 |
A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a p...
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WO/2016/114853A1 |
An insert (360) for combustion air holes (327) in a liner wall (319) of a combustion chamber (320) is disclosed. The insert (360) includes a body (362), a flange (361) extending from the body (362), and a restarter jet (370). The restart...
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WO/2016/113495A1 |
The invention relates to a turbine engine combustion assembly (20), which includes: an annular flame tube (21) including a front wall (23), a rear wall (24) and a bottom (22) arranged facing an engine shaft (30); an injection wheel (41) ...
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WO/2016/113684A1 |
A system (62) for controlling flame instability comprising: a nozzle (66) coupled to a fuel supply line (70), an insulation housing (74) coupled to the nozzle, a combustor (78) coupled to the nozzle via the insulation housing, where the ...
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WO/2016/108477A1 |
Provided are a high-voltage application-type combustor and a method for applying an electric field by means of the same combustor, the high-voltage application-type combustor comprising: a premix chamber (410) arranged on an upper end of...
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WO/2016/103231A2 |
A supporting member for thermoinsulating tiles of gas turbine combustion chambers comprises an elongated plate (10), having a coupling head (12) at a first end, the coupling head (12) being structured to couple with a thermoinsulating ti...
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WO/2016/104725A1 |
The present invention provides a burner, a combustor equipped with the burner, and a gas turbine, with which it is possible to premix a first hydrocarbon-based fuel (for example, natural gas), a second fuel (for example, hydrogen gas), a...
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WO/2016/105327A1 |
A method for reducing defects on a component (105) having at least a substrate (116), a thermal barrier coating layer (112) over the substrate (116), and cooling holes (100) through the substrate and the thermal barrier coating layer (11...
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WO/2016/103230A1 |
A fuel supply system (3) for supplying fuel to a combustion chamber (2) provided with at least a burner assembly (5) is provided with at least one feed line (7) comprising: a manifold (8) supplied with fuel; at least one connecting pipe ...
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WO/2016/095157A1 |
Disclosed is a combustion chamber (10) having a porous flame tube (14), comprising a combustion chamber housing (12) and at least one flame tube (14) surrounded by the combustion chamber housing (12), wherein the combustion chamber housi...
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WO/2016/099805A2 |
The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wa...
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WO/2016/096388A1 |
A combustor for a gas turbine is described. The combustor comprises a combustor liner (3), a metering plate (7) attached to an end of the combustor liner and a combustor casing (5) at least partially surrounding the combustor liner (3). ...
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WO/2016/093430A1 |
A swirler assembly comprises: a base plate; a plurality of vanes arranged along the circumferential direction of the base plate; a cover plate arranged so as to cover the vanes; and air spray holes that penetrate through an outer surface...
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WO/2016/093829A1 |
A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a tra...
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WO/2016/093429A1 |
A swirler assembly comprises: a base plate; and a plurality of vanes which are arranged apart from each other along the circumferential direction of the base plate, wherein each of the vanes is provided with a gas fuel accommodating port...
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WO/2016/094035A1 |
A connection system (10) for a combustor assembly (12) of a turbine engine (14) whereby the connection system (10) includes a transition cylinder (18) with a transition cylinder cooling system (16) is disclosed. The connection system (10...
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WO/2016/093566A1 |
The present invention relates to a combustor comprising: an outer case which has a receiving space formed on the inside thereof in a cylindrical shape, has an opening portion formed at one side thereof, and has a blocking plate formed at...
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WO/2016/087780A1 |
In order to improve the mixing of oxidizing air within an injection system (42) with which a turbo machine combustion chamber (18) is equipped, there is proposed an air intake ring (56) the annular deflection wall (66) or venturi of whic...
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WO/2016/088783A1 |
This combustor comprises: a cylindrical tail pipe which has an inlet for combustion gas at one end thereof, has an outlet for the combustion gas at the other end thereof, and discharges the combustion gas introduced from the inlet throug...
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WO/2016/088833A1 |
A sprayed-coating formation method equipped with: a step for preparing a spray target member having a surface in which one end of a plurality of holes opens; a step for preparing a plurality of masking pins comprising a metal; an inserti...
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WO/2016/089341A1 |
The present disclosure provides a gas turbine combustor including a combustion structure (10) having a combustor liner (14) and a flow sleeve (12). The combustor liner (14) includes inner and outer surfaces (31, 30) and defines a combust...
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WO/2016/088612A1 |
Provided are a gas turbine combustor and a gas turbine, with which the amount of NOx exhaust emissions from a diffuse combustion-type duct burner can be reduced. A duct burner 36 is provided with cylindrical fuel injection nozzles 38 and...
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WO/2016/087110A1 |
A liquid fuel lance (156) for a burner (30) of a combustor (16) of a gas turbine combustor, a liquid fuel system incorporating the liquid fuel lance and a method of operating the liquid fuel system are disclosed. The liquid fuel lance (1...
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WO/2016/085494A1 |
Apparatus and method for a combustion turbine engine are provided. The apparatus includes a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) ofthe lance. At least onejet in cross- flow injector (18) may be dispo...
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WO/2016/084111A1 |
The present invention concerns a multistage hybrid system for the induction, anchorage and stabilization of distributed flame in advanced combustors for gas turbine, comprising: a) a swirler (13), bearing on the input side a plurality of...
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WO/2016/079720A1 |
A lance injector for injecting fuel into a combustion chamber (2) of a gas turbine comprises: a coaxial first tubular body (15) and second tubular body (16); a nozzle (20) connected to respective first ends (15a, 16a) of the first tubula...
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WO/2016/080957A1 |
A transition duct exit frame (10) for supporting a transition duct (12) extending downstream from a combustor (14) to a turbine assembly (16) in a gas turbine engine (18) and including one or more transition duct exit frame inserts (20) ...
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WO/2016/079223A1 |
The invention relates to a thermal energy machine (1), in particular a gas turbine (2), comprising a compressor (3) for compressing an air mass flow (5) flowing along the machine longitudinal central axis (6) in an axial flow direction (...
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WO/2016/079221A1 |
The invention relates to a diffuser (1) of a thermal energy machine (3), in particular of a gas turbine (5), comprising a diffuser inlet (20), a diffuser outlet (22), and a plurality of air-guiding elements (23), wherein an air mass flow...
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WO/2016/076856A1 |
Disclosed are an arrangement of a casing component and a combustor component, a method of attaching a casing component to a combustor component, and an engine including the arrangement. The arrangement includes a spanner nut which retain...
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WO/2016/076852A1 |
Disclosed are a combustor arrangement, a method of attaching a casing component to a combustor component, and an engine. The combustor arrangement includes a combustor component including a flange, a casing component arranged on the comb...
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WO/2016/072423A1 |
A burner (6) for injecting a mixture of fuel and air from the proximal end side, which is set away from a combustion chamber (48), to the distal end side, which is near the combustion chamber (48), wherein the burner (6) is provided with...
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WO/2016/071186A1 |
The invention relates to a burner assembly (1) comprising a combustion chamber (2), a plurality of mixing ducts (3) leading into the combustion chamber (2), in which mixing ducts, during intended operation, introduced combustion air (4) ...
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WO/2016/069339A1 |
A fuel injector (310) for a combustor (300) of a gas turbine engine (100) is disclosed. The fuel injector (310) includes a flange (312), a fitting boss (315), a stem (320), a gas fuel passage (322), a gas fuel fitting (317), and a gas he...
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WO/2016/068922A1 |
A pilot burner (15) and method for stabilizing a pilot flame in a combustor (14) of a gas turbine engine are provided. The pilot burner includes a fuel nozzle (17) having at least one orifice having a cross-sectional profile effective to...
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