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Patent Searching and Data


Matches 401 - 450 out of 12,742

Document Document Title
WO/2016/093429A1
A swirler assembly comprises: a base plate; and a plurality of vanes which are arranged apart from each other along the circumferential direction of the base plate, wherein each of the vanes is provided with a gas fuel accommodating port...  
WO/2016/094035A1
A connection system (10) for a combustor assembly (12) of a turbine engine (14) whereby the connection system (10) includes a transition cylinder (18) with a transition cylinder cooling system (16) is disclosed. The connection system (10...  
WO/2016/093566A1
The present invention relates to a combustor comprising: an outer case which has a receiving space formed on the inside thereof in a cylindrical shape, has an opening portion formed at one side thereof, and has a blocking plate formed at...  
WO/2016/087780A1
In order to improve the mixing of oxidizing air within an injection system (42) with which a turbo machine combustion chamber (18) is equipped, there is proposed an air intake ring (56) the annular deflection wall (66) or venturi of whic...  
WO/2016/088783A1
 This combustor comprises: a cylindrical tail pipe which has an inlet for combustion gas at one end thereof, has an outlet for the combustion gas at the other end thereof, and discharges the combustion gas introduced from the inlet thr...  
WO/2016/088833A1
A sprayed-coating formation method equipped with: a step for preparing a spray target member having a surface in which one end of a plurality of holes opens; a step for preparing a plurality of masking pins comprising a metal; an inserti...  
WO/2016/089341A1
The present disclosure provides a gas turbine combustor including a combustion structure (10) having a combustor liner (14) and a flow sleeve (12). The combustor liner (14) includes inner and outer surfaces (31, 30) and defines a combust...  
WO/2016/088612A1
Provided are a gas turbine combustor and a gas turbine, with which the amount of NOx exhaust emissions from a diffuse combustion-type duct burner can be reduced. A duct burner 36 is provided with cylindrical fuel injection nozzles 38 and...  
WO/2016/087110A1
A liquid fuel lance (156) for a burner (30) of a combustor (16) of a gas turbine combustor, a liquid fuel system incorporating the liquid fuel lance and a method of operating the liquid fuel system are disclosed. The liquid fuel lance (1...  
WO/2016/085494A1
Apparatus and method for a combustion turbine engine are provided. The apparatus includes a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) ofthe lance. At least onejet in cross- flow injector (18) may be dispo...  
WO/2016/084111A1
The present invention concerns a multistage hybrid system for the induction, anchorage and stabilization of distributed flame in advanced combustors for gas turbine, comprising: a) a swirler (13), bearing on the input side a plurality of...  
WO/2016/079720A1
A lance injector for injecting fuel into a combustion chamber (2) of a gas turbine comprises: a coaxial first tubular body (15) and second tubular body (16); a nozzle (20) connected to respective first ends (15a, 16a) of the first tubula...  
WO/2016/080957A1
A transition duct exit frame (10) for supporting a transition duct (12) extending downstream from a combustor (14) to a turbine assembly (16) in a gas turbine engine (18) and including one or more transition duct exit frame inserts (20) ...  
WO/2016/079223A1
The invention relates to a thermal energy machine (1), in particular a gas turbine (2), comprising a compressor (3) for compressing an air mass flow (5) flowing along the machine longitudinal central axis (6) in an axial flow direction (...  
WO/2016/079221A1
The invention relates to a diffuser (1) of a thermal energy machine (3), in particular of a gas turbine (5), comprising a diffuser inlet (20), a diffuser outlet (22), and a plurality of air-guiding elements (23), wherein an air mass flow...  
WO/2016/076856A1
Disclosed are an arrangement of a casing component and a combustor component, a method of attaching a casing component to a combustor component, and an engine including the arrangement. The arrangement includes a spanner nut which retain...  
WO/2016/076852A1
Disclosed are a combustor arrangement, a method of attaching a casing component to a combustor component, and an engine. The combustor arrangement includes a combustor component including a flange, a casing component arranged on the comb...  
WO/2016/072423A1
A burner (6) for injecting a mixture of fuel and air from the proximal end side, which is set away from a combustion chamber (48), to the distal end side, which is near the combustion chamber (48), wherein the burner (6) is provided with...  
WO/2016/071186A1
The invention relates to a burner assembly (1) comprising a combustion chamber (2), a plurality of mixing ducts (3) leading into the combustion chamber (2), in which mixing ducts, during intended operation, introduced combustion air (4) ...  
WO/2016/069339A1
A fuel injector (310) for a combustor (300) of a gas turbine engine (100) is disclosed. The fuel injector (310) includes a flange (312), a fitting boss (315), a stem (320), a gas fuel passage (322), a gas fuel fitting (317), and a gas he...  
WO/2016/068922A1
A pilot burner (15) and method for stabilizing a pilot flame in a combustor (14) of a gas turbine engine are provided. The pilot burner includes a fuel nozzle (17) having at least one orifice having a cross-sectional profile effective to...  
WO/2016/064391A1
A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burne...  
WO/2016/063222A1
A gas turbine unit including a combustion chamber provided with a plurality of burner assemblies and a supply system, configured to supply fuel to the burner assemblies. Each burner assembly includes a respective lance injector (20) havi...  
WO/2016/061654A1
A combustor with pressure gain, intermittent combustion and substantially continuous discharge flow for use in gas turbine engines in general, in ramjet engines in general and in gas turbine engines for aircraft propulsion in particular,...  
WO/2016/063222A9
A gas turbine unit including a combustion chamber (5) provided with a plurality of burner assemblies (15) and a supply system (8), configured to supply fuel to the burner assemblies (15). Each burner assembly (15) includes a respective l...  
WO/2016/062581A1
The invention relates to a heat shield element (1) comprising a wall (2) having a hot side (3) and an opposing cold side (4), a peripheral edge (5) having an inner side (6) and an outer side (7), and a securing device (8) arranged substa...  
WO/2016/063791A1
A combustor according to the present invention is provided with: a pilot burner (15) disposed along an axis (P); a plurality of pre-mixing burners (16) each of which has a pre-mixing swirler cylinder (19) and a pre-mixing nozzle (20) dis...  
WO/2016/059200A1
A method for reducing NOx emissions in a gas turbine in which a flow of primary air and a flow of fuel are fed into a dual annular counter rotating swirler (4), said primary air flow being fed into the inner and outer annular chambers (5...  
WO/2016/058903A1
The invention relates to a fuel nozzle body (1) comprising a rearward end (2) and a front end (3) comprising an outer tube (4) which extends from the rearward end (2) to the front end (3) and has radial openings (5) for a first fuel (6) ...  
WO/2016/061101A1
The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is uti...  
WO/2016/056180A1
A fuel injecting device (36) for a combustor (12) has a pilot burner (40) and a main burner (4). The main burner (4) has at least one first fuel injection port (41a) to supply a first fuel to an upstream section of a combustion chamber (...  
WO/2016/057009A1
A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (12), and a plurality of mains ...  
WO/2016/056580A1
Provided is a turbine stator blade cooling structure that can suppress the use of compressed air. Also provided is a gas turbine engine that is provided with the turbine stator blade cooling structure. A turbine blade cooling structure t...  
WO/2016/057010A1
Disclosed are a clamping ring, a combustor arrangement including a clamping ring, a method of attaching a casing component to a combustor component, a method for the removal of a plurality of radially extending tabs on a combustor compon...  
WO/2016/056521A1
A combustor (3) equipped with: a plurality of first burners extending along an axis (P) and arranged in the circumferential direction with an interval interposed therebetween; a substrate (31) having support openings formed therein for s...  
WO/2016/056579A1
Provided is a combustor that has an efficient cooling structure. Also provided is a gas turbine engine that is provided with the combustor. A combustor that is for a gas turbine and that is provided with a combustion cylinder and with a ...  
WO/2016/051067A1
The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by...  
WO/2016/051758A1
A gas turbine (100) according to the present invention uses hydrogen gas as a fuel, has a fuel injection nozzle (23), and is provided with: a combustor (20), at the interior of which a combustion chamber (24) is formed; a water-vapor sup...  
WO/2016/051757A1
 A fuel injection nozzle (31) according to the present invention is provided with: a premixing flow passage (34) for mixing fuel (103) and air (102) to generate a gas mixture; and an injection port (33) positioned downstream of the pre...  
WO/2016/050530A1
The invention relates to a rotating machine component (2), particularly a gas turbine combustion component, comprising at least one part (25) built from a porous material (15) com¬ prising a plurality of pores (16), wherein at least a s...  
WO/2016/050535A1
The invention relates to a heat shield element (50) for a heat shield (24) of a combustion chamber (10), comprising a hot side (32) which can be exposed to hot gas, an opposite cold side (34), and peripheral sides (36a, 36b); the heat sh...  
WO/2016/051756A1
 A fuel injector (23) is provided with a cylindrical flow passage (32) opening in a combustion chamber (26), a fuel introduction passage (34) for guiding the fuel toward the combustion chamber (26) of the cylindrical flow passage (32),...  
WO/2016/050575A1
The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal, the part (2) compris...  
WO/2016/047393A1
A combustor comprising a nozzle, a burner cylinder (43) surrounding the outer perimeter of the nozzle, and an outside flowpath cylinder (60) surrounding the outer perimeter of a downstream end section in the burner cylinder (43). A purge...  
WO/2016/047397A1
A sound attenuator (30) having a plate section forming a combustion cylinder (20) and an acoustic cover (34) forming, in conjunction with this plate section, a space on the outside perimeter of the combustion cylinder (20). An aperture (...  
WO/2016/047601A1
A burner (3) is provided with: a transition pipe (30) within which a channel is formed; and an inner tube (20) inserted into the transition pipe (30) from the upstream side of the channel so that a combustion gas is blown into the channe...  
WO/2016/045779A1
The invention relates to a burner head (36) for a burner (35) and to a gas turbine (30) having a burner (35) comprising a burner head (36) of said type. The burner head (36) extends along a burner longitudinal axis (1) and comprises at l...  
WO/2016/047624A1
A combustor (3) is provided with: a combustor main body having a tail pipe (30) having a flow passage formed on the inner side thereof, and an inner cylinder (20) inserted inside the tail pipe (30) from the upstream side of the flow pass...  
WO/2016/046074A1
The invention is directed to a burner 1 comprising of a burner axis 8, provided with a fuel and an oxygen comprising gas supply section 4 at an upstream end 5 and a burner front section 2 at a downstream end 3. The burner front section 2...  
WO/2016/042960A1
A combustion burner comprises: a nozzle; a swirl vane that has a fuel injection hole for injecting fuel, is provided around the nozzle in an annular air flow channel extending along the axial direction of the nozzle, and is configured so...  

Matches 401 - 450 out of 12,742