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Matches 1 - 50 out of 12,528

Document Document Title
WO/2018/217485A1
A refractory ceramic component (10) for a gas turbine engine (100) is employed that is more cost effective than typical components used in the gas turbine engine (100). The refractory ceramic component (10) may include a refractory ceram...  
WO/2018/212761A1
A method for staging premixers in a combustion system for a gas turbine having a compressor section and a turbine section. The method includes providing a plurality of burners each including premixers wherein compressed air from the comp...  
WO/2018/212760A1
A combustion system for a gas turbine. The system includes a cowl having a dome portion and side portions that form an open end. Compressed air from a turbine compressor flows in a first air flow path adjacent the cowl. A liner is locate...  
WO/2018/212001A1
Provided is a gas turbine combustor (3) equipped with a fuel injection device (15) that has a plurality of annular fuel injection parts (25), each having numerous fuel injection ports (25a) formed therein, the gas turbine combustor being...  
WO/2018/203939A2
A trapped vortex combustor for use in a gas turbine engine includes an outer vortex chamber wall and a dome attached to, or formed integrally with, the outer vortex chamber wall. The dome, the outer vortex chamber wall, or both define at...  
WO/2018/203153A1
An engine that uses detonation for generating energy includes a housing (300); an inlet (306) configured to inject a fuel mixture (304) into an ignition region (320) of the housing (300), the inlet being attached to the housing (300); an...  
WO/2018/202350A1
The invention relates to a silo combustion chamber comprising a vertically extending flame tube that can be lit from above and through which circulation takes place in a downward motion, the outer surface of the flame tube being provided...  
WO/2018/202407A1
The invention relates to a combustion chamber (1), comprising a support structure (3) surrounding a combustion space (2) and comprising an inner lining, which is formed from a plurality of heat shield elements fastened to the support str...  
WO/2018/199237A1
The thermal barrier coating is provided with a ceramic layer (120) formed on a heat-resistant alloy substrate and containing ceramic substance. The ceramic layer (120) has: a first dense layer (121); an intermediate porous layer (122) la...  
WO/2018/199289A1
A fuel injector (1) comprises: a fuel supply tube (8); a plurality of premixing tubes (2); a support plate (3) that supports the fuel supply tube (8) and the plurality of premixing tubes (2); a board (4) that supports downstream-side end...  
WO/2018/190926A1
The present disclosure is directed to a combustor assembly for a propulsion system. The combustor assembly includes an annular inner liner extended generally along the longitudinal direction. The combustor assembly further includes an an...  
WO/2018/189481A1
The invention relates to a self-adapting gas turbine firebox with variable geometry, comprising at least one system with a variable opening for automatically adjusting a configuration of the combustion inside a combustion chamber (101) a...  
WO/2018/189944A1
A regenerative cooler (2) is provided with a flow passage forming structure (10) having formed therein a fuel flow passage (11) to which liquid fuel is supplied. A coating (12, 12A) at least partially covering a wall surface of the fuel ...  
WO/2018/184078A2
Tesla's three-phase hybrid rotary internal combustion engine is based on theoretical essentials of Tesla's concept of internal combustion engines and the principles of transforming kinetic fluid energy into mechanical work applied on Tes...  
WO/2018/184078A3
Tesla's three-phase hybrid rotary internal combustion engine is based on theoretical essentials of Tesla's concept of internal combustion engines and the principles of transforming kinetic fluid energy into mechanical work applied on Tes...  
WO/2018/180773A1
Provided is a combustion device equipped with: an ammonia supply unit (6) that, by supplying primary reduction ammonia as a nitrogen oxide reducing agent to within a combustor (2) and mixing secondary reduction ammonia with combustion ex...  
WO/2018/181063A1
This combustion device (C) causes the combustion of fuel ammonia and combustion air within a combustion chamber (N), and is equipped with a combustor liner (3a) which forms the combustion chamber, a burner (3c) which is attached to one e...  
WO/2018/181030A1
This combustion device (C) is equipped with a compressor (2a) for compressing combustion air, a combustor (2b) for causing the combustion of fuel ammonia and the compressed combustion air, and an ammonia injection unit (3) for injecting ...  
WO/2018/181002A1
This combustion device (C) is provided with a combustor (3) for causing the combustion of fuel ammonia and combustion air within a combustion chamber (N), and the combustor is equipped with a cooling ammonia supply unit (3g) for mixing t...  
WO/2018/181559A1
The present invention addresses the problem of providing a thermal barrier coating film (13) which exhibits high durability even in a gas turbine used in a molten salt environment such as a heavy oil fired gas turbine, and which can be f...  
WO/2018/180984A1
This combustion device uses combustion air to cause the combustion of fuel ammonia within a combustor (2), and is equipped with a catalyst reduction unit (4) for reducing nitrogen oxides in combustion exhaust gas supplied from the combus...  
WO/2018/183078A1
A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus (22, 70) is subject to a hot-temperature combustion flow received from a combustor basket and may include a liner (72) includ...  
WO/2018/173659A1
A resonant sound absorber for a gas turbine combustor, comprising a plurality of resonance chambers provided independently of each other aligned in the axial direction of the gas turbine combustor so as to communicate with a gas flow pat...  
WO/2018/172653A1
A turbine ring assembly comprising ring sections (10) forming a turbine ring (1) and a ring support structure (3), each ring section (10) having, along a section plane defined by an axial direction (DA) and a radial direction (DR) of the...  
WO/2018/173122A1
This combustor 20 comprises a tubular combustor liner 70, and a fuel nozzle 21A that is provided to one end of the combustor liner 70 and that sprays fuel and an oxidant into the combustor liner. The fuel nozzle 21A is provided with a pl...  
WO/2018/168747A1
Provided is a combustor nozzle equipped with a nozzle main body (2) extending along an axis, said nozzle main body (2) being equipped with: a first fuel passage (21) formed along the axis (Am) and through which a first fuel (F1) flows; f...  
WO/2018/169506A1
Thermal stresses in fuel injector nozzles in combustors or burners for combustion or gas turbine engines are modeled, in order to identify thermal stress concentrations, and normalize them spatially and temporally. The modeled first fuel...  
WO/2018/169507A1
A fuel injection nozzle for a combustion turbine engine has thermal stress-relief vanes, which accommodate and relieve localized thermal stresses within its monolithic, three-dimensional nozzle structure, imparted by heat transfer during...  
WO/2018/167913A1
Provided is a transition piece that can suppress the generation of a large thermal stress in a fixed part of a support post and that can easily achieve replacement of the support post. This transition piece guides combustion gas generate...  
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 ...  

Matches 1 - 50 out of 12,528