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Matches 1 - 50 out of 11,500

Document Document Title
WO/2017/048455A1
A turbine engine combustion system is disclosed including a fuel nozzle assembly having three independently controlled stages of water injection. A first stage includes water mixed with a gaseous fuel upon inlet to the nozzle, where the ...  
WO/2017/045014A1
An internal combustion engine wherein a thermo potential heat flow in combustion is maximized by providing a feedback of an optimized amount of thermo potential heat flow that is modulated in the exhaust media, into the air intake, and a...  
WO/2017/045823A1
The invention is related to a turbomachine component (1), particularly a gas turbine combustor component or burner component, comprising a body (2) with a first (20), a second (21) and a third section (22), the first, second and third se...  
WO/2017/047516A1
The objective is to enable the portion of a combustor tube where the temperature rises to be cooled efficiently, and to improve the reliability of a combustor tube without reducing the efficiency of a gas turbine. Therefore, this combust...  
WO/2017/048851A1
A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body...  
WO/2017/045820A1
The invention relates to a turbomachine component (1), particularly a gas turbine burner, comprising a solid body (2) with an elongated clearance (3). Furthermore it comprises a channel (4) located within the clearance (3) of that body (...  
WO/2017/042250A1
An improved combustion system (200) with at least one improved combustion chamber (202) is disclosed. The at least one improved combustion chamber (202) comprises one or more improved liners (204) having one or more jet holes (206). The ...  
WO/2017/042493A1
The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion c...  
WO/2017/039567A1
A combustor transition duct (110) comprising a main duct portion (113) having a primary opening and a secondary opening, wherein a first axis extends from a center of the primary opening to the secondary opening; an extension flange (115...  
WO/2017/036665A1
The invention relates to a method for manufacturing and assembling a metal body (1) on a metal carrier (4), the body having multiple surfaces (3) separated by edges (2), wherein an unfolded form (5) of the body (1) is produced from a met...  
WO/2017/034539A1
A modular combustor system (10) for a combustion turbine engine and method regarding the modular combustor system are provided. The modular combustor system includes a spool-shaped piece (12). A combustor can (14) is connected to the spo...  
WO/2017/032424A1
The invention relates to a heat shield element (01) for a heat shield (21) for use in a combustion chamber (26) of a gas turbine. Said heat shield element comprises a wall (03) which has a hot side (04) and a cold side (05) opposite the ...  
WO/2017/034435A1
A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a premixing chamber formed between an outer annular shroud and an inner annular hub, a number of swirler vanes disposed about th...  
WO/2017/034537A1
Apparatus and method for a combustion turbine engine are provided. A pre-mixing passage (24) has an upstream inlet arranged to receive a flow of air to be mixed with fuel. A fuel-injecting lance (12) is disposed in the pre-mixing passage...  
WO/2017/029090A1
The invention relates to a tubular combustion chamber (22) for a gas turbine (1), comprising at least one burner arrangement (11), a housing wall (24) which surrounds the combustion chamber interior and has a flame tube (20) and a transi...  
WO/2017/029101A1
A premixed dual fuel burner includes a burner head, a burner interior elongated along a main axis and having an upstream side enclosed by a swirler and a downstream side enclosed by a premixing section, and an injection component. The bu...  
WO/2017/025232A1
The invention relates to a combustion chamber having a combustion chamber wall (12, 25) which is clad at least in certain regions with a number of heat shield elements secured to the combustion chamber wall. The combustion chamber accord...  
WO/2017/025295A1
The invention relates to a pilot burner with a burner lance (32) for a gas turbine, wherein the burner lance extends along a longitudinal axis (36) and has a lance tip (35) on one end on the combustion chamber side, wherein the lance tip...  
WO/2017/025294A1
The invention relates to a combustion chamber (10) for a gas turbine (1) having a combustion chamber wall (12, 24) surrounding the hot gas path of the combustion chamber (10) and at least one burner arrangement (11) for discharging a fla...  
WO/2017/025284A1
The invention relates to a combustion chamber (10, 22, 22a) for a gas turbine (1), having a combustion chamber casing (12, 25) that surrounds the hot gas path of the combustion chamber and, for protection from hot gases, is clad at least...  
WO/2017/021268A1
Intelligent Control of combustion with time series and by- pass filters The present invention describes a method for predicting a combustion error type of a combustion flame burning in a combustion chamber of the combustion system for a ...  
WO/2017/023325A1
A trailing edge duct (110) is used with gas turbine engines. The trailing edge duct (110) is unitary in shape and has improved aerodynamics. The trailing edge duct (110) has a trailing edge (120) that is able to provide improved support ...  
WO/2017/022397A1
A gas turbine fuel flow rate setting device (100) is provided with a flow rate ratio computing unit (160) and a flow rate computing unit (180). The flow rate ratio computing unit (160) accepts a parameter (CLCSO) correlated to the gas tu...  
WO/2017/023331A1
A ducting arrangement (10), including: an annular duct (38) having a plurality of discrete integrated exit pieces (IEP 18) secured together to form the annular duct and an annular chamber (14) configured to deliver an annular flow of com...  
WO/2017/018983A1
Combustor system and method for reducing combustion residence time and/or damping combustion dynamics are provided. The system includes a first main burner (12) that in turn includes a first fluidic nozzle (16) tuned to convey a first fl...  
WO/2017/018992A1
A multi-fuel nozzle for a combustion turbine engine and method regarding such a multi-fuel nozzle are provided. The nozzle includes a support flange (12). A first fuel-injecting stage (14) defines a first conduit extending along a longit...  
WO/2017/018982A1
An improved gas turbine combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustion system includes a flow-accelerating structure (16, 51), such as a transition duct, having an ...  
WO/2017/013318A1
The main subject of the invention is a combustion chamber (1) for a turbomachine (10), comprising a chamber end wall (16) and a plurality of air and fuel injection systems (21) distributed circumferentially about an axis (T) of the combu...  
WO2016200459A3
A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion c...  
WO2017008963A1
The invention relates to a burner for a gas turbine engine (10), wherein the burner (30) comprises a combustion chamber (28) and a swirler (107) adapted to guide a swirler air flow (125) to the combustion chamber (28), wherein the swirle...  
WO2017009247A1
The invention relates to a burner for a gas turbine (10), wherein the burner (30) comprises a combustion chamber (28), a preheating device adapted to preheat air before it enters the combustion chamber (28) and a swirler (107) adapted to...  
WO/2017/006971A1
A combustor is provided with a combustion cylinder having a first region in which at least one first opening is formed, a nozzle configured so that fuel is jetted into the combustion cylinder, and a first acoustic device attached to the ...  
WO/2017/007068A1
A combustor comprises: a combustion can in the form of a can having a combustion space where fuel is combusted, the combustion can including an inlet through which fuel is introduced, an outlet through which gas produced from the combust...  
WO/2017/006690A1
A combustor nozzle, a gas turbine combustor, a gas turbine, a cover ring, and a method for manufacturing a combustor nozzle, wherein there are provided: a nozzle body (71) to which a fuel channel (72) is provided; a cover ring (75) dispo...  
WO/2017/005694A1
The invention relates to a burner for a gas turbine (10), wherein the burner (30) comprises a combustion chamber (28), a first injector (103) adapted to inject a first fuel into the combustion chamber (28) and a second injector (104) ada...  
WO/2017/006063A1
The invention relates to a turbine engine combustion chamber including: an outer annular housing; a flame tube (20) connected to the outer housing, said flame tube (20) including an inner annular wall (20b) and an outer annular wall (20a...  
WO/2017/002075A3
Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial in...  
WO/2017/003417A1
An ion sensor (15) is placed in a combustor that is capable of detecting irregular combustion conditions. The ion sensor (15) may be a disc or ring that is placed within the chamber wall of the combustor. Detection of ions by the ion sen...  
WO/2017/003421A1
An arrangement (14) including: a wall (34) having raised ribs (36) defining a perimeter (66) and a plurality of pockets (52) within the perimeter; a stud (100) extending from the wall into a respective pocket; a cover sheet (12) disposed...  
WO/2017/003649A1
A system includes a fuel nozzle including a first wall disposed about a central axis, a second wall disposed about the first wall, and a plurality of lobes disposed between the first and second walls, wherein the plurality of lobes is sp...  
WO/2017/002076A1
Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combusto...  
WO/2017/003458A1
A hybrid metal-reinforced ceramic matrix composite (CMC) material component is provided having a body (12) including a ceramic matrix composite material (14) and a metal skeleton structure (18) encompassing at least a portion of the body...  
WO/2017/002074A1
Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a r...  
WO/2016/209222A1
A cooling ring (102) of a combustor basket system (110) has a transition zone 108 that extends to a cooling channel (106) at a cooling channel entrance (104). The transition zone (108) has the substantially the same material strength thr...  
WO/2016/209101A1
A fuel nozzle assembly for use in a gas turbine includes a center body, an outer tube that at least partially surrounds the center body, a premix flow passage that is defined radially between the center body and the outer tube, and a ...  
WO/2016/207117A1
A method for the combustion of ammonia, wherein a first combusion chamber (2) receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas such as air. Combustion of the ammonia and hydrogen produces nitrogen oxi...  
WO/2016/208998A1
A method for controlling a gas turbine combustor, according to one embodiment for achieving the objective of the present invention, may comprise: a detection step of obtaining combustion oscillation values through first detection units p...  
WO/2016/208952A1
A fuel supply nozzle unit disclosed herein comprises: a fuel supply nozzle that includes a front end portion having a plurality of fuel supply holes formed therein, a rear end portion extending from the front end portion and having a thr...  
WO/2016/204534A1
A combustion duct assembly for a gas turbine, according to the present invention, comprises: a liner at which a combustor is disposed at the upper side thereof and an annular spring seal protruding outward is attached to the outer surfac...  
WO/2016/203540A1
A structure for the rear part of a jet engine has an axis. The structure comprises: a casing surrounding a duct about the axis and open axially forward and rearward; a cone having a pointed rear end, the cone forming a first angle relati...  

Matches 1 - 50 out of 11,500