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Matches 1 - 50 out of 11,460

Document Document Title
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...  
WO/2017/021268A1
Intelligent Control of combustion with time series and by- pass filters The present invention describes a method for predicting a combustion error type of a combustion flame burning in a combustion chamber of the combustion system for a ...  
WO/2017/023325A1
A trailing edge duct (110) is used with gas turbine engines. The trailing edge duct (110) is unitary in shape and has improved aerodynamics. The trailing edge duct (110) has a trailing edge (120) that is able to provide improved support ...  
WO/2017/022397A1
A gas turbine fuel flow rate setting device (100) is provided with a flow rate ratio computing unit (160) and a flow rate computing unit (180). The flow rate ratio computing unit (160) accepts a parameter (CLCSO) correlated to the gas tu...  
WO/2017/023331A1
A ducting arrangement (10), including: an annular duct (38) having a plurality of discrete integrated exit pieces (IEP 18) secured together to form the annular duct and an annular chamber (14) configured to deliver an annular flow of com...  
WO/2017/018983A1
Combustor system and method for reducing combustion residence time and/or damping combustion dynamics are provided. The system includes a first main burner (12) that in turn includes a first fluidic nozzle (16) tuned to convey a first fl...  
WO/2017/018992A1
A multi-fuel nozzle for a combustion turbine engine and method regarding such a multi-fuel nozzle are provided. The nozzle includes a support flange (12). A first fuel-injecting stage (14) defines a first conduit extending along a longit...  
WO/2017/018982A1
An improved gas turbine combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustion system includes a flow-accelerating structure (16, 51), such as a transition duct, having an ...  
WO/2017/013318A1
The main subject of the invention is a combustion chamber (1) for a turbomachine (10), comprising a chamber end wall (16) and a plurality of air and fuel injection systems (21) distributed circumferentially about an axis (T) of the combu...  
WO2016200459A3
A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion c...  
WO2017008963A1
The invention relates to a burner for a gas turbine engine (10), wherein the burner (30) comprises a combustion chamber (28) and a swirler (107) adapted to guide a swirler air flow (125) to the combustion chamber (28), wherein the swirle...  
WO2017009247A1
The invention relates to a burner for a gas turbine (10), wherein the burner (30) comprises a combustion chamber (28), a preheating device adapted to preheat air before it enters the combustion chamber (28) and a swirler (107) adapted to...  
WO/2017/006971A1
A combustor is provided with a combustion cylinder having a first region in which at least one first opening is formed, a nozzle configured so that fuel is jetted into the combustion cylinder, and a first acoustic device attached to the ...  
WO/2017/007068A1
A combustor comprises: a combustion can in the form of a can having a combustion space where fuel is combusted, the combustion can including an inlet through which fuel is introduced, an outlet through which gas produced from the combust...  
WO/2017/006690A1
A combustor nozzle, a gas turbine combustor, a gas turbine, a cover ring, and a method for manufacturing a combustor nozzle, wherein there are provided: a nozzle body (71) to which a fuel channel (72) is provided; a cover ring (75) dispo...  
WO/2017/005694A1
The invention relates to a burner for a gas turbine (10), wherein the burner (30) comprises a combustion chamber (28), a first injector (103) adapted to inject a first fuel into the combustion chamber (28) and a second injector (104) ada...  
WO/2017/006063A1
The invention relates to a turbine engine combustion chamber including: an outer annular housing; a flame tube (20) connected to the outer housing, said flame tube (20) including an inner annular wall (20b) and an outer annular wall (20a...  
WO/2017/003417A1
An ion sensor (15) is placed in a combustor that is capable of detecting irregular combustion conditions. The ion sensor (15) may be a disc or ring that is placed within the chamber wall of the combustor. Detection of ions by the ion sen...  
WO/2017/003421A1
An arrangement (14) including: a wall (34) having raised ribs (36) defining a perimeter (66) and a plurality of pockets (52) within the perimeter; a stud (100) extending from the wall into a respective pocket; a cover sheet (12) disposed...  
WO/2017/003649A1
A system includes a fuel nozzle including a first wall disposed about a central axis, a second wall disposed about the first wall, and a plurality of lobes disposed between the first and second walls, wherein the plurality of lobes is sp...  
WO/2017/002076A1
Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combusto...  
WO/2017/003458A1
A hybrid metal-reinforced ceramic matrix composite (CMC) material component is provided having a body (12) including a ceramic matrix composite material (14) and a metal skeleton structure (18) encompassing at least a portion of the body...  
WO/2017/002074A1
Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a r...  
WO/2016/209222A1
A cooling ring (102) of a combustor basket system (110) has a transition zone 108 that extends to a cooling channel (106) at a cooling channel entrance (104). The transition zone (108) has the substantially the same material strength thr...  
WO/2016/209101A1
A fuel nozzle assembly for use in a gas turbine includes a center body, an outer tube that at least partially surrounds the center body, a premix flow passage that is defined radially between the center body and the outer tube, and a ...  
WO/2016/207117A1
A method for the combustion of ammonia, wherein a first combusion chamber (2) receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas such as air. Combustion of the ammonia and hydrogen produces nitrogen oxi...  
WO/2016/208998A1
A method for controlling a gas turbine combustor, according to one embodiment for achieving the objective of the present invention, may comprise: a detection step of obtaining combustion oscillation values through first detection units p...  
WO/2016/208952A1
A fuel supply nozzle unit disclosed herein comprises: a fuel supply nozzle that includes a front end portion having a plurality of fuel supply holes formed therein, a rear end portion extending from the front end portion and having a thr...  
WO/2016/204534A1
A combustion duct assembly for a gas turbine, according to the present invention, comprises: a liner at which a combustor is disposed at the upper side thereof and an annular spring seal protruding outward is attached to the outer surfac...  
WO/2016/203540A1
A structure for the rear part of a jet engine has an axis. The structure comprises: a casing surrounding a duct about the axis and open axially forward and rearward; a cone having a pointed rear end, the cone forming a first angle relati...  
WO/2016/198792A1
The invention mainly relates to a turbine engine combustion chamber module (4) comprising at least one constant-volume combustion chamber (7). Said module is characterized in that it also comprises, upstream of said at least one constant...  
WO/2016/193069A1
The present invention describes a method for controlling an engine vibration of a gas turbine engine (110). The engine vibration of the gas turbine engine (110) is measured. The measured engine vibration is compared with a threshold valu...  
WO/2016/193589A1
The invention relates to an annular wall of a turbine engine combustion chamber, including between a cold side (16a, 18a) and a hot side (16b, 18b), a plurality of air-inlet openings (30) distributed according to at least one circumferen...  
WO/2016/193068A1
A combustor for a gas turbine engine comprising a central axis (44) a bout which is arranged in flow sequence a radial swirler (40), a pre-chamber (60) partly defined by a wall (62) and a combustion chamber (38). The radial swirler (40) ...  
WO/2016/188954A1
A gas turbine fuel nozzle (1) for a combustor of a gas turbine engine comprises a sleeve (2) with an internal duct (3) for premixed fuel gas flow; it further comprises a flame ionization sensor (4) located on the sleeve (2) externally to...  
WO/2016/190510A1
A combustion liner includes air guiding caps which are respectively engaged to a mounting member and are turned in a flow direction of air so as to collect a fluid flowing around the combustion liner and feed it to the combustion liner, ...  
WO/2016/186423A1
The disclosed invention relates to a fuel supply nozzle for injecting fuel into a burner. The fuel supply nozzle has the shape of a tube having an outer wall surface and an inner wall surface, which extend from a root to a tip, and compr...  
WO/2016/181307A1
The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which...  
WO/2016/182785A1
A grommet (341) for a combustion chamber (320) of a gas turbine engine (100) is disclosed. The grommet (341) includes a lower platform (352) and a collar (351). The lower platform (352) includes a plurality of top slots (347) located in ...  
WO/2016/178664A1
An improved layout of cooling fluid conduits in a turbine transition duct is provided. The transition duct (10) may include a transition body made with a multi-panel arrangement (12, 14) that defines a passage to route a hot combustion g...  
WO/2016/173920A1
The invention relates to a hot gas-conducting casing (7) comprising a hot gas duct (8) of annular cross section, wherein the hot gas duct (8) is bounded inwardly by a casing inner wall (9) and outwardly by a casing outer wall (10) provid...  
WO/2016/174175A1
A gas turbine drive system in mechanical drive configuration is described. The gas turbine drive system comprises a gas turbine engine (1) drivingly connected to a driven turbomachine (3). The gas turbine engine includes a dry low NOx em...  
WO/2016/174363A1
The invention relates to a combustion chamber of a turbomachine, comprising: an annular outer casing; and a flame tube connected to the outer casing, said flame tube comprising an annular inner wall and an annular outer wall defining a f...  
WO/2016/167700A1
The present invention relates to a liquid propellant chemical rocket engine reactor Thermal Management System (TMS), which system comprises a reactor comprising a thermally conductive reactor housing, a heat bed, and a catalyst bed, whic...  
WO/2016/167784A1
A flexible interface system (10) for a combustor (12) of a gas turbine engine (14) in which a flexible extension (16) is configured to enable radial movement of a combustor basket liner (22) relative to a combustor basket (24) while main...  
WO/2016/162239A1
A segmented annular combustor (10) for a gas turbine engine (1), axially extending between a first axial burner end (11) and a second axial outlet end (12) and radially extending between an annular inner liner (15) and an annular outer l...  
WO/2016/162248A1
The invention relates to a burner arrangement (1) for a combustion chamber, in particular a gas turbine combustion chamber, for burning fluid fuels, having a main burner (2) and a pilot burner (3) which is arranged centrally therein and ...  

Matches 1 - 50 out of 11,460