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Matches 1 - 50 out of 11,899

Document Document Title
WO/2017/154976A1
A fuel control device equipped with a trunk fuel valve degree-of-opening determination unit, a branch line flow rate determination unit, and a correction amount determination unit. The trunk fuel valve degree-of-opening determination uni...  
WO/2017/154900A1
A gas turbine combustor and a gas turbine, wherein there are provided a combustor outer cylinder (41), a combustor inner cylinder (42), a pilot nozzle (53) and a main nozzle (56) disposed in the combustor inner cylinder (42), an air chan...  
WO/2017/155914A1
A ducting arrangement (30) in a combustion system of a gas turbine engine is provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-ac...  
WO/2017/154821A1
This burner assembly of a combustor is equipped with: a plurality of first nozzles arranged in the circumferential direction of the combustor; a plurality of first burner cylinders which accommodate the plurality of first nozzles; and in...  
WO/2017/154729A1
In the present invention multiple cooling flow paths (35) are formed between the outer surface and the inner surface of a combustor panel. The cooling flow paths (35) have inlets (36i) that open at the outer surface and introduce a cooli...  
WO/2017/148843A1
The invention relates to a flow element (1) for fluidic contact with a hot gas flow (15) within an aircraft engine, wherein the flow element (1) comprises a base material (2), which has a hot gas surface (12) facing the gas flow (15) and...  
WO/2017/150419A1
This combustor (3) comprises: a first cylindrical body (11) that holds a fuel nozzle that extends in the direction of an axial line (Ac), and that has air flowing therethrough toward the downstream side; a second cylindrical body (12) th...  
WO/2017/150364A1
A combustion device is provided with a nozzle casing that defines an axial channel, and a nozzle disposed inside the axial channel. The nozzle includes: a cylindrical nozzle body extending along the axial channel; a swirler vane projecti...  
WO/2017/150664A1
This acoustic device (4) is provided with: a porous plate (32) having, on one plate-thickness-direction side, a plurality of holes (34) which pass through in the plate thickness direction and through which a main current flows; and a hou...  
WO/2017/142707A1
A method for predicting an anomaly in a combustor (16) is presented. The method includes receiving signals representative of parameters in one or more combustion cans (22, 24) of the combustor, generating a plurality of patterns based on...  
WO/2017/141510A1
Provided is a joined structure that has joining sections 15 in which a plurality of cylinders 11, 12 formed of a ceramic-based composite material are joined with each other via intermediate materials 16 by abutting end surfaces 11B, 12A ...  
WO/2017/139222A1
A fuel injector (32) for a combustion engine (10) includes an injector body (34) having formed therein a first passage (50) structured to feed a fuel to an outlet (40) of the injector body (34), and a second passage (52) structured to fe...  
WO/2017/138813A1
The invention provides an assembly (100) for the injection of fuel into the combustion chamber of an internal combustion engine comprising an actuator (1) with a drive shaft (2), an engagement means (4), and a rotary fuel injector compri...  
WO/2017/134843A1
An aviation component (1) used in an aviation gas turbine engine, wherein the aviation component (1) is provided with: an annular part (5) having an outer peripheral surface; a flange part (6) formed at one axial end part of the annular ...  
WO/2017/133819A1
The invention relates to a gas turbine combustion chamber comprising an inner combustion chamber wall (2) and an outer combustion chamber wall (3) that form an annular combustion chamber; air blending holes (4) are distributed along the ...  
WO/2017/134844A1
Provided is an aircraft component used in a gas turbine engine for an aircraft, the aircraft component comprising an annular part having an outer peripheral surface, and a boss part (7) that radially protrudes from the outer peripheral s...  
WO/2017/127255A1
A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straigh...  
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/2017/119993A3
Can-annular burners (50) for gas turbine engines with flow conditioners having locally varying, asymmetrical patterns of circumferential perforations, to promote uniform fuel-air mixture among all premixers (54) in the burner basket (58)...  
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...  

Matches 1 - 50 out of 11,899