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Matches 1 - 50 out of 12,422

Document Document Title
WO/2018/164775A1
A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an ...  
WO/2018/162995A1
The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to util...  
WO/2018/158045A1
The invention relates to a method for the assembly and/or disassembly of burners (2) of a gas turbine with a combustion chamber, in particular an annular combustion chamber, and/or of hot-gas-carrying elements (7) of a combustion chamber...  
WO/2018/160229A1
A combustor (100) for a turbine engine includes an inner combustion liner (104) and an outer combustion liner (106) together defining at least in part an interior (108). The interior includes a combustion chamber (110) and a main portion...  
WO/2018/156419A1
An axially staged combustion system includes a primary fuel nozzle, a primary combustion zone defined downstream from the primary fuel nozzle, a conical duct disposed downstream from the primary combustion zone and an integrated exit pie...  
WO/2018/155496A1
A combustor equipped with, as main burners (16), first burners (16A) for circulating primary air and generating an air-fuel mixture, and second burners (16B) for circulating primary air in the direction opposite that of the first burners...  
WO/2018/156423A1
An endcover assembly for a combustor includes an endcover and a fuel nozzle rigidly connected to the endcover. The fuel nozzle includes a plurality of tubes that extends axially through a first plate, a fuel plenum and a second plate whe...  
WO/2018/147837A1
A gas turbine engine (100) has a circumferential staging configuration of fuel injectors in a combustor. As a turbine blade revolves within the gas turbine engine it is subjected to lift and drag forces based on the configuration of lit ...  
WO/2018/147933A1
A rotating detonation combustion system includes an outer wall and an inner wall together defining at least in part a combustion chamber and a combustion chamber inlet. A nozzle of the rotating detonation combustion system is located at ...  
WO/2018/147951A1
A gas turbine engine includes a liner positioned within a compressor section or a turbine section of the gas turbine engine and at least partially defining a core air flowpath through the gas turbine engine. The gas turbine engine also i...  
WO/2018/144006A1
A desired steady-state, fuel-air ratio of a fuel and air mixture is normalized within a combustor (100) for a combustion turbine engine, by selectively varying, at any location about the three-dimensional volume (160) within its premixer...  
WO/2018/141627A1
The invention relates to a burner arrangement (1) comprising a plurality of mixing channels (4) which extend parallel to the main axis (2) of the burner arrangement (1) and are arranged in at least two concentric circles (3), in which mi...  
WO/2018/144065A1
An air-cooled component for a combustion turbine, having a monolithic, three-dimensional lattice structure (250) of selectively oriented metallic webs (212, 214, 216) with locally varying lattice density, and asymmetrical- and serpentine...  
WO/2018/143168A1
This combustion device (C) uses fuel air to combust a fuel within a combustion chamber (N), wherein the combustion device comprises a reducing agent injection device for injecting a reducing agent toward a flame within the combustion cha...  
WO/2018/144008A1
A combustor for a combustion turbine engine incorporates a fuel and air premixer, embodiments of which locally vary structure of one or more of air ducts, fuel delivery passages, fuel and air mixing ducts, and/or fuel and air discharge d...  
WO/2018/144064A1
An air-cooled panel (200) for a combustion turbine engine includes, a first planar, metallic sheet (202), having an outer side and an opposed inner side. A monolithic, three-dimensional lattice structure (210), having a first face, is bo...  
WO/2018/139131A1
A natural gas fired combined-cycle power generation system is provided with: a vaporization device, a cooling device, a circulation flow path, a pump, and a gas-turbine combined power generation device. The vaporization device includes: ...  
WO/2018/140173A1
Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turb...  
WO/2018/140135A1
Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine port...  
WO/2018/137895A1
The invention relates to a fastening screw (26) for a heat shield element (14b) which is provided for use in a combustion chamber (4) of a gas turbine (1), comprising a screw shank (28) and a screw head (30). Arranged in the region of th...  
WO/2018/140136A1
Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including ...  
WO/2018/134501A2
The invention relates to a turbomachine combustion chamber, configured to be housed in a chamber housing of said turbomachine, which housing is provided with an air supply, said combustion chamber being delimited by at least a first subs...  
WO/2018/134058A1
The invention relates to a burner tip (19) for installation in a burner (11), wherein the burner tip (19) has a surface (OF) facing a combustion chamber (BR), an air channel structure (21) leading to the surface (OF) and defining an air ...  
WO/2018/133292A1
A nozzle with adjustable inner and outer flow channel equivalence ratios comprises a central cylinder (6), an outer-wall cylinder (3), and a wave swirler (5). The wave swirler (5) is coaxially disposed in the outer-wall cylinder (3). The...  
WO/2018/132241A1
The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle incl...  
WO/2018/132185A1
A field configurable support housing assembly (10) is provided. The support housing assembly comprises a support housing base (20) and a cylindrical hollow fuel rocket (40). The support housing base (20) includes at least one through hol...  
WO/2018/130765A1
The invention relates to a combustion chamber (6) for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine, comprising: - a radially outer annular shroud (11), - a radially inner annular shroud (12), coaxia...  
WO/2018/131142A1
This embodiment of a transition piece introduces combustion gas that is generated inside a liner inner tube of a combustor liner, which has a double pipe structure comprising the liner inner tube and a liner outer tube, into a turbine. T...  
WO/2018/131654A1
This control system regulates the flow rate of heating water supplied to a fuel heating device which heats gas turbine fuel, to control the temperature of the fuel supplied to a combustor of a gas turbine via the fuel heating device. The...  
WO/2018/127471A1
The invention relates to a burner tip (19) for a pilot burner, which can be used for example in a gas turbine. The invention also relates to a method for additively producing a burner tip (19) of this kind for example by means of selecti...  
WO/2018/128599A1
A gas turbine engine (10) has a combustor basket (15) that has resonators (25). Resonator bases (26) are attached directly to the outer surface (22) of a combustor liner (20). A thermal barrier coating (23) is applied to the internal sur...  
WO/2018/128600A1
A gas turbine engine (10) has a side seal (25a) located between adjacent exit pieces. The side seal (25a) comprises a first seal side (23a) and a second seal side (24a) that contact each other. The first seal side (23a) has a spring (26a...  
WO/2018/118466A1
A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) including a pilot fuel nozzle is provided. The fuel manifold may include stage fuel galleries (16, 18), and fuel feed bosse...  
WO/2018/116975A1
The present invention provides a plurality of main nozzles (34) of a combustor, the main nozzles (34) being provided spaced apart in a circumferential direction on an outer circumferential side of a pilot nozzle. The main nozzles (34) ea...  
WO/2018/118282A1
A combustion liner or component produced through the use of additive manufacturing techniques. The combustion liner or other component may be formed having a feature based optimized cooling circuit at least partially embedded in the thic...  
WO/2018/114918A1
The invention relates to a burner tip (19), suitable for use in a pilot burner, e.g. in a gas turbine. The invention further relates to a method for producing the burner tip (19) by an additive production process such as selective laser ...  
WO/2018/111558A1
A fuel distribution manifold (330) for a gas turbine engine (100) is disclosed herein. The fuel distribution manifold (330) includes a manifold body (331), a stage divider (332), and a plurality of manifold outlet ports (301-312). The st...  
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...  

Matches 1 - 50 out of 12,422