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Matches 251 - 300 out of 12,739

Document Document Title
WO/2017/103232A1
In order to provide a combustion chamber device which is easy to produce and allows a reliable operation, it is proposed that the combustion chamber device comprises the following: a burner head for the supply of fuel and/or oxidator to ...  
WO/2017/098782A1
This fuel cell system is provided with: a fuel cell; an electric compressor that supplies a cathode gas to the fuel cell; a cathode exhaust gas passage through which flows a cathode exhaust gas discharged from the fuel cell; a turbine pr...  
WO/2017/097606A1
The invention relates to a combustion chamber (1) having a carrier structure (2) and a heat shield (3) which is formed by a plurality of heat shield elements (4) arranged on the carrier structure (2) with the aid of securing means (5), s...  
WO/2017/100270A1
A method directs fuel-oxidant premix into a reaction zone through a first total premix inlet flow area, and causes the premix to combust and form a stable flame projecting into a process chamber through an outlet from the reaction zone. ...  
WO/2017/095358A1
An improved interface (111) between a combustion basket ring and a transition assembly (113) in a can-annular gas turbine engine. Traditionally, a spring clip is positioned within a circumferential gap between a combustion basket ring an...  
WO/2017/094965A1
Disclosed is a device for diagnosing a combustion state of a gas turbine. The device for diagnosing a combustion state of a gas turbine according to the present invention comprises: a combustion diagnosis tube in which one end thereof is...  
WO/2017/091318A1
A fuel nozzle including vortex generating features for use in a combustion turbine engine is provided. An array of inner pre-mixing conduits (20) extends between an inlet end (14) and an outlet end (16) of the nozzle. An array of outer p...  
WO/2017/090221A1
According to the present invention, a transition structure between a combustor and a turbine in a gas turbine is provided with a transition piece including a duct and a flange projecting from a downstream edge of the duct, and a piece co...  
WO/2017/084656A2
The aim of the invention is to significantly increase the electrical efficiency or the proportion of the effective work of gas turbines, even in small gas turbines or microsize gas turbines having a simple design. According to the invent...  
WO/2017/085683A2
A method of reconditioning and fabricating turbine components is provided. In one embodiment, the method is performed on a fuel nozzle assembly of a gas turbine, and comprises providing a pre-assembled fuel nozzle assembly having a base,...  
WO/2017/084656A3
The aim of the invention is to significantly increase the electrical efficiency or the proportion of the effective work of gas turbines, even in small gas turbines or microsize gas turbines having a simple design. According to the invent...  
WO/2017/085683A3
A fuel nozzle assembly for a gas turbine and a method of reconditioning fuel nozzle assemblies is provided. The method is performed on a fuel nozzle assembly (100) of a gas turbine, and comprises providing a pre-assembled fuel nozzle ass...  
WO/2017/082876A1
A gas engine turbine has a trailing edge duct (110) that is used for the transition duct. The trailing edge duct (110) has an extension flange (115) located at its outlet (117). The extension flange (115) has a contoured receiving sectio...  
WO/2017/077955A1
In a combustion cylinder, a gas turbine combustor, and a gas turbine according to the present invention: an outer-side region of a cooling part that is a region on the outer side relative to a reference line (L1) which runs through the c...  
WO/2017/078516A1
The present invention relates to fuel injectors in general and rotating fuel injectors for internal combustion engines in particular. The rotating or rotary fuel injector according to the present invention comprises a higher dynamic axia...  
WO/2017/072451A1
To improve air/fuel mixing at low speed, the invention concerns an aerodynamic injection system (30) for a combustion chamber (8) of an aircraft turbine engine, the system comprising a central body (70) comprising a first air circulation...  
WO/2017/074343A1
An improved combustion system in a combustion turbine engine is provided. The combustor system may include an injector assembly (12) disposed in a combustion stage disposed downstream from a main combustion stage (18) of the combustor sy...  
WO/2017/074345A1
An improved combustion system in a combustion turbine engine is provided. The combustor system may include an injector assembly (12) disposed in a combustion stage disposed downstream from a main combustion stage of the combustor system....  
WO/2017/067775A1
The present invention relates to a combustor (100) for a gas turbine. The combustor (100) comprises a pre-combustion chamber (101), a swirler (103), a burner plenum (26), wherein the swirler (103) and the burner plenum (26) surround the ...  
WO/2017/065038A1
[Problem] To invent an engine system as a means for reducing CO2 and NOX emissions to cope with global warming. [Solution] An engine system wherein a combustion chamber unit configured so as to have a step in which enriched oxygen and hy...  
WO/2017/065285A1
Provided is an engine (10) having a gas turbine unit and multiple combustion units (80) for supplying combustion gas (51) to the gas turbine unit. Each of the combustion units (80) includes: a combustion chamber (11); a first mechanism (...  
WO/2017/060819A1
The present disclosure relates to a method and apparatus to mitigate thermo-acoustic instabilities in combustor of gas turbine engines using a lean premixed flame; and provides a dynamic control strategy for mitigating thermo-acoustic in...  
WO/2017/060605A1
The invention relates to a ring-shaped combustion chamber (10) comprising a first ring-shaped wall (12) and a second ring-shaped wall (13) which are coaxial about an axis (X), a chamber bottom (14) connecting the first and second walls (...  
WO/2017/055074A1
A combustion chamber (18) of a thermodynamic cycle turbine with a recuperator, for producing electrical energy, comprising a casing (56) that houses a flame tube (64) with a perforated diffuser for the passage of hot compressed air, a pr...  
WO/2017/055187A1
The invention relates to a burner assembly (1) comprising a housing (3), which defines an annular combustion chamber (2), and multiple burners (4), which open into the annular combustion chamber (2). Each burner (4) is arranged in a thro...  
WO/2017/058155A1
Provided is a way of implementing impingement cooling for a gas turbine engine. Instead of welding the impingement sheets (10a-10i) to an integrated exit piece (15), the impingement sheets (10a-10i) are attached in a way that takes advan...  
WO/2017/052795A3
Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combust...  
WO/2017/051346A1
This disclosure describes an improved method of electron beam ("EB") welding utilizing a collection pocket (118). The method includes providing a first surface (110,146) and a second surface (100,132,140,144), forming a collection pocket...  
WO/2017/052795A2
Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combust...  
WO/2017/052547A1
A dual stage vane pilot nozzle (100) has a non-diffusion nozzle (110) and a first fuel stage (121) and a second fuel stage (122). The first fuel stage (121) has a first fuel injector (101) having first injection holes (103) and a first f...  
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...  

Matches 251 - 300 out of 12,739