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Matches 201 - 250 out of 12,741

Document Document Title
WO/2017/170227A1
Provided is a combustor equipped with: a nozzle main body (16) having a shaft body (24) extending along an axial line, and swirl blades (26) that extend from the outer circumferential surface of the shaft body (24) in the radial directio...  
WO/2017/170485A8
A combustor (3) is provided with: a first nozzle (51) extending along an axis (Ac) and injecting fuel to the downstream side; a flame stabilizer (52C) for covering the downstream end of the first nozzle (51) from the outer peripheral sid...  
WO/2017/170476A1
A combustor (3) is provided with: a fuel nozzle for injecting fuel; a tubular body (24) that has a tubular shape in which a combustion region through which combustion gas flows is formed inside, and in which a plurality of slits (50) are...  
WO/2017/169950A1
This gas turbine combustor is provided with: a plurality of swirling cylinders (31) that are arranged within a combustor liner (11) and that impart a swirling flow to a premixed gas (Fp) comprising fuel and combustion air mixed in advanc...  
WO/2017/170209A1
Provided is a gas turbine in which a first nozzle (1) comprises first nozzle inner diameter-side fuel injection holes (13) for injecting a first nozzle fuel and first nozzle outer diameter-side fuel injection holes (14) that are for inje...  
WO/2017/165611A1
The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending...  
WO/2017/165581A1
The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle por...  
WO/2017/165092A1
The present disclosure is directed to an annular combustion system. The annular combustion system includes an inner liner and an outer liner that define there between an annulus that circumscribes a centerline of the combustion system. T...  
WO/2017/165876A3
A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner ...  
WO/2017/157631A1
The invention relates to a combustion chamber (18) of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy, said combustion chamber comprising a housi...  
WO/2017/158038A1
In accordance with one embodiment, a system is presented. The system includes a casing (36), a combustor (12) disposed within the casing (36), and a sensing device (38) located on the casing (36) and configured to sense a plurality of ac...  
WO/2017/158636A1
A gas turbine apparatus 10 according to an embodiment is provided with: a combustor casing 70; a combustor 20 disposed in the casing; a tubular body 80 surrounding the combustor 20 and demarcating a space between the combustor casing 70 ...  
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...  

Matches 201 - 250 out of 12,741