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Matches 1 - 50 out of 12,316

Document Document Title
WO/2018/094536A1
The present disclosure generally relates to rotary turbomachinery methods and integrated processes requiring high-energy efficiency. In one embodiment, the present invention relates to rim-rotor configurations enabling long-term survival...  
WO/2018/098157A2
A fuel burner includes a tube extending from a first end to a second end and having an outer surface and an inner surface defining a central passage. The central passage is supplied at the first end with a mixture of air and combustible ...  
WO/2018/090383A1
A nozzle (12) of a combustion chamber of a gas turbine engine, the nozzle comprising: a main nozzle member (20) forming an internal fuel gas channel (24) and a fuel gas outlet (26) in fluid communication with the fuel gas channel (24). T...  
WO/2018/090384A1
A combustion chamber of a gas turbine engine. The combustion chamber comprises: an annular flame pipe (10), wherein the annular flame pipe (10) forms an annular combustion cavity (14), and the annular combustion cavity (14) defines an ax...  
WO/2018/087878A1
A combustor liner (11) that is used in a gas turbine combustor and that forms a combustion chamber (13) is provided with: an outside wall (21) that is made of a metal material; a panel (25) that is made of a ceramic matrix composite and ...  
WO/2018/088184A1
The gas turbine plant is provided with a gas turbine (10), a heating device (60), a decomposition gas line (70), and a decomposition gas compressor (85). The heating device (60) heats ammonia so that the ammonia is pyrolyzed and decompos...  
WO/2018/082538A1
A method of optimizing a premix fuel nozzle (12) for a gas turbine is provided. When the gas turbine is in operation, the nozzle (12) comprises an axial flow field of air and fuel mixture flowing through a burner tube (25) and around a n...  
WO/2018/082539A1
A nozzle tip (24) for a premix fuel nozzle (12, 22) is provided. The nozzle tip (24) includes an outer body (26) having an outer body external face (36) facing the downstream end of a burner tube (25). The outer body external face (36) h...  
WO/2018/084943A1
A combustor of an industrial gas turbine engine having a combustor secured within a combustor casing with a combustor cavity surrounding the combustor, and a flow liner forming a cooling air space between the casing and the flow liner in...  
WO/2018/080474A1
A liner (10) for a gas turbine engine is inserted into a channel (12) located in a inlet ring (11) of a transition duct (8). The liner is formed as a flat unitary piece with angled ends (14). The angled ends complement each other. When i...  
WO/2018/078350A1
A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between ...  
WO/2018/075854A1
An apparatus for assisting with the combustion of fuel includes a swirler assembly and a fuel nozzle. Fuel from a fuel nozzle fuel reservoir is directed into a fuel nozzle mixing zone and combines with air inside the fuel nozzle mixing z...  
WO/2018/072970A1
The invention relates to an improved ceramic heat shield (155) for a gas turbine (100). The ceramic heat shield (155) has a porous ceramic body (11) and according to the invention an infiltration coating (12) that is provided in a surfac...  
WO/2018/071074A3
A deflector for a gas turbine engine combustor. The combustor includes a liner defining a combustion zone and a mixer assembly configured to supply the combustion zone with a predetermined mixture of fuel and air. The deflector includes ...  
WO/2018/071260A1
A gas turbine engine includes a compressor section and turbine section. The gas turbine engine of the present disclosure is a relatively small gas turbine engine, configured to generate less than 1491 kW (2,000 horsepower) during peak op...  
WO/2018/068980A1
The invention relates to a heat shield element (01) for use in a heat shield of a combustion chamber. The heat shield element (01) comprises a ceramic tile element (11) and a metallic carrier element (31). For fastening purposes, the til...  
WO/2018/067253A1
A combustion management device for generating a thrust burst to impart a physical impulse. In operation, a combustion chamber, defined by a valve unit (33), is primed to a set pressure and fueled by fuel injectors (23). An ignitor (22) t...  
WO/2018/060200A1
Cooled machine component, particularly a turbomachine component, comprising a body (2) with at least one integrated cooling channel (40) for guiding a cooling fluid through an interior of the body, the cooling channel comprising a lattic...  
WO/2018/059804A1
The invention is related to a gas turbine arrangement for at least dual fuel operation, comprising a plurality of fuel manifolds (21,22,23), each connected to each of at least one combustor (12) and a control system (17). A first manifol...  
WO/2018/060054A1
A method for controlling pilot-fuel/pilot-air ratio provided to a burner of a combustion system for altering its operating point is presented. First, a value of a first parameter e.g. temperature, is checked, and if the value equals or e...  
WO/2018/060098A1
A pilot burner assembly for a combustion volume in a gas turbine engine is presented. The pilot burner assembly includes a pilot burner, a pilot-fuel supply line, and a pilot-air supply line. The pilot burner has a burner face that inclu...  
WO/2018/063151A1
A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air f...  
WO/2018/060044A1
A swirler for creating a swirling fuel/air mix is presented. The swirler has vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air...  
WO/2018/056994A1
A turbine engine can have an atomizer having two orifices that form an intersecting spray cone. The turbine engine can also have an atomizer that has three orifices that forms a partially filled spray cone. The intersecting sprays cones ...  
WO/2018/055325A1
A combined combustor and recuperator is formed with the recuperator surrounding the combustor. Cold gas conduits (14, 16, 20) through the recuperator follow along involute paths toward the combustor. Hot has conduits (26) through the rec...  
WO/2018/054918A1
A pilot burner assembly for a combustion chamber in a gas turbine engine is presented. The pilot burner assembly includes a pilot burner and a radial swirler. On a burner head face of the pilot burner, pilot fuel injection holes are pres...  
WO/2018/050999A1
The invention relates to a combustion chamber (40) for a turbine engine which comprises an annular wall (12) defining an inner space (11) of the chamber, a film of wall-cooling air (28) along the annular wall (12) in the inner space, com...  
WO/2018/044367A3
A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, ...  
WO/2018/041647A1
The invention is directed to a burner (1) of a turbomachine, particularly a gas turbine engine, comprising an upstream burner section (2) for providing a first fuel and/or an oxygen containing fluid to an upstream end of a burner interio...  
WO/2018/041454A1
The present invention relates to a turbine, in particular a turbine with heat exchanger for producing energy, in particular electrical energy, comprising at least one compression stage (12) with at least one gas compressor (14), a cross-...  
WO/2018/041455A1
The present invention relates to a combustion chamber (10) of a turbine, in particular a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, in particular electrical energy, comprising a casing (12) with an...  
WO/2018/044266A1
An impingement cooling system for a gas turbine engine includes an initial impingement surface (10) with a centrally located opening (12). A plurality of channels (14) and plurality of sub-channels (22) extends radially outward from the ...  
WO/2018/038792A1
A fuel-air mixer assembly (52) that includes a mixer portion, and a flare cup portion (60) coupled to the mixer portion. The flare cup portion includes a side wall (68) that including an inlet opening and a discharge opening (72) defined...  
WO/2018/025294A1
This combustor 20 comprises: a combustor liner 61 that is provided in a combustor casing 70; a cylindrical body 80 that partitions the space between the combustor casing 70 and the combustor liner 61; piping 42 that guides combustion gas...  
WO/2018/026419A3
A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The com...  
WO/2018/026579A1
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...  
WO/2018/026382A1
Injector assemblies (12) and ducting arrangement including such injector assemblies are provided. The injector assembly may include a reactant-guiding structure arranged to convey a flow of reactants (19) into the combustion stage and me...  
WO/2018/026381A1
A combustion system in a combustion turbine engine is provided. The system may include a combustor wall (40) fluidly coupled to receive a cross-flow of combustion products (21). The combustor wall (40) may include a plurality of cooling ...  
WO/2018/021996A1
A gas turbine engine has a resonator ring (10) that is formed by two circumferentially extending rings. The first and second circumferentially extending rings (30, 31) have located within them baffles (20). Both the first ring (30) and t...  
WO/2018/011827A1
A swirl mesh lean direct injection concept for distributed flame holding for low pollutant emissions and mitigation of combustion instability. The invention further relates to a new method for flame holding with least pressure drop and f...  
WO/2018/012327A1
The present invention provides a structure in which an operative gas (A) of a gas turbine engine (GT) is used as a cooling medium (CL) to cool a constituent member of the gas turbine engine, wherein a wall surface (13a) of a flow channel...  
WO/2018/009418A1
A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surfa...  
WO/2018/009411A3
A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combu...  
WO/2018/009411A2
A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combu...  
WO/2018/003488A1
This gas turbine combustor comprises: a casing which is coupled to a main housing; a liner which has an interior in which a combustion chamber extending in the axial direction is formed, the liner comprising an upstream portion, includin...  
WO/2018/004097A1
The present invention relates to: a transition piece assembly having improved cooling efficiency for cooling a high-temperature region formed on the side surface of a transition piece; and a combustor including the same, and provides a t...  
WO/2018/001696A1
The invention relates to a heat shield assembly (01) of a combustion chamber, comprising a supporting structure (03) and heat shield elements (11) arranged on the supporting structure (03). For fastening, the supporting structure (03) ha...  
WO/2018/005889A3
The present disclosure generally relates to methods for additive manufacturing (AM) that utilize integrated ribs (224) to support thin walled annular structures (220). An annular wall (220) fabricated using AM has a thickness less than 0...  
WO/2017/218217A1
The present disclosure is directed to a fuel injector assembly of a gas turbine engine, including a centerbody, an outer sleeve surrounding the centerbody, an inner sleeve disposed between the centerbody and at least a section of the out...  
WO/2017/217622A1
The present invention relates to an air guide cap for guiding airflow to a through hole on the bottom. The air guide cap comprises: an upper surface upwardly inclined with respect to a horizontal plane; and wall surfaces extending downwa...  

Matches 1 - 50 out of 12,316