Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 11,623

Document Document Title
WO/2017/121872A1
The present invention relates to a combustor (100) for a gas turbine, comprising: a pre-combustion chamber (101) having a peripheral wall (115) around a centre axis (35) of the pre-combustion chamber (101), the peripheral wall (115) comp...  
WO/2017/123982A1
A catalytic ignition system (10) includes a gas fuel supply (12) and a catalytic igniter (14) that is in fluid communication with the gas fuel supply. The catalytic igniter comprises a metallic shell (18), a catalyst (20) disposed within...  
WO/2017/123619A1
A fuel nozzle assembly includes a center body comprising an outer sleeve and an internal fuel passage defined within the outer sleeve. Tire internal fuel passage defines a fuel flow path within the center body and includes an inlet defin...  
WO/2017/120039A1
A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes two primary tubes, a secondary tube (603), a primary gas gallery (643), and a secondary gas gallery (644). The two primary tubes are conn...  
WO/2017/120037A1
A center body assembly (700) for a fuel injector (600) is disclosed. The center body assembly (700) defines a primary liquid passage (721), a liquid gallery, swirl slots (775), and a prefilm passage (769). The primary liquid passage (721...  
WO/2017/119993A2
Can-annular burners (28, 50) for gas turbine engines (20) with flow conditioners (42, 62, 72, 82) having locally varying, asymmetrical patterns of circumferential perforations (44, 64), to promote uniform fuel-air mixture among all premi...  
WO/2017/120035A1
A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes a flange assembly (610) with a distribution block (612), three main gas tubes, and an injector head (630). The distribution block (612) e...  
WO/2017/120038A1
A method for lean direct injection of a liquid fuel from a fuel injector (600) into a combustion chamber (390) of a gas turbine engine (100) is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber (...  
WO/2017/116243A1
A combustor assembly lift track comprises one or more rails comprising one or more portions that combine to extend in a non-linear path and a rail connector attached to at least one of the one or more portions of the one or more rails, w...  
WO/2017/116242A1
A combustor assembly lift arm (220) comprises a moveable support arm comprising a first end and a second end with a combustor assembly engagement frame (240) connected to the first end of the moveable support arm, wherein the combustion ...  
WO/2017/116266A1
A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel por...  
WO/2017/116244A1
A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combus...  
WO/2017/110971A1
This gas turbine engine (GE), which burns, in a combustion chamber (3), a compressed gas compressed by a compressor (1), and drives a turbine (5) by means of the obtained combustion gas, is provided with: a compressed gas supply part (17...  
WO/2017/110955A1
A fuel injection device (1) for injecting a mixture of fuel and air into a combustion chamber (E) inside the combustor (CB) of a gas turbine engine, wherein the fuel injection device (1) is provided with a fuel injection valve (3) having...  
WO/2017/111262A1
A streamer induction type combustor for improving flame stability according to one embodiment of the present invention may comprise: a combustion chamber in which combustion occurs; a high voltage supply which is installed outside the co...  
WO/2017/110973A1
A gas turbine engine (GT) provided with: a plurality of combustors (3) disposed at an incline toward the radially outward side from the turbine side toward the compressor side; and a diffuser inner tube (25) and outer tube (27) forming a...  
WO/2017/110104A1
The present invention reduces the thermal stress of flanges which join a combustor casing and a turbine casing together. This gas turbine (10) is provided with a compressor (14), a combustor (15), and a turbine (16) along the extension d...  
WO/2017/108454A1
The present invention relates to a combustor (100) for a gas turbine comprising: a pre-combustion chamber (101), a swirler (103), a pilot burner (110) upstream the pre-combustion chamber (101) which comprises a pilot burner surface (111)...  
WO/2017/111889A1
A gas turbine engine has attached thereto a transducer (45) for transmitting ultrasonic waves through the premix injector (10) and the combustion chamber (35). The transducer (45) may be a piezoelectric transducer. Ultrasonic waves may b...  
WO/2017/111041A1
The main fuel injection section of a fuel injection device has: a main outer air flow passage for taking in compressed air from an inlet open radially outward; a main inner air flow passage for taking in compressed air from an inlet open...  
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...  

Matches 1 - 50 out of 11,623