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WO/2012/011830 |
The invention relates to devices for igniting fuel, specifically to gaseous and gas-droplet detonation, and can be used for transmitting a shaped detonation wave to the unit or mechanism using said wave in various technological devices a...
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WO/2012/004496 |
The invention relates to an ignition procedure for a turbine engine combustion chamber (10) supplied with fuel by injectors (26) and comprising means (28) for igniting the fuel injected into the chamber (10). This procedure comprises: an...
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WO/2012/004131 |
The present invention discloses a combustion apparatus (100), which comprises a combustion chamber (12), in which combustion of a fuel/oxidant mix takes place, a pre-chamber (14) located upstream of the combustion chamber (12), a first d...
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WO/2012/000732 |
The present invention discloses a combustion apparatus (100), which comprises a first device (10) for mixing a fuel with an oxidant, a combustion chamber (12) in which combustion of the fuel/oxidant mix takes place, a pre-chamber (14) lo...
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WO/2012/001141 |
The invention relates to a burner assembly for a gas turbine, comprising at least one combustor, a centrally arranged pilot burner and a plurality of main burners (107) surrounding the pilot burner, wherein each main burner (107) compris...
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WO/2012/000712 |
The invention relates to a burner module, comprising a plate (90) consisting of an upper face (92) and a lower face (91), wherein at least two cavities containing fuel (110) are provided in the lower face (91), and wherein a through-pass...
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WO/2012/000792 |
The present invention discloses a fuel injection duct (100) for a combustion apparatus which comprises an inlet opening (10), an outlet opening (20), and an inner surface, wherein the inner surface exhibits a surface structure (30) impar...
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WO/2011/163289 |
Emissions and combustion dynamics of a turbine engine are managed through a combustor system that injects water into the primary fuel flow and supplies a secondary water steam to the flame zone of the combustor through a central, seconda...
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WO/2011/157548 |
A damping device (122; 222; 322; 422; 522) for damping pressure oscillations within a combustion chamber (106; 206; 306; 406; 506) of a turbine (102; 202; 302; 402; 402; 502) comprises a radially extending damping device body (123; 223; ...
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WO/2011/157458 |
The invention relates to a secondary feed unit and a primary feed unit which comprises a primary mixing tube (11) and a fuel nozzle (1) having a fuel nozzle outlet (4), wherein the fuel nozzle (1) and the primary mixing tube (11) are arr...
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WO/2011/156871 |
An assembly (10) comprising: an engine (12) having a compressor (13) coupled via a shaft (14) to a turbine (15), the engine (12) having an inlet; a heat exchanger (20) having a radiant heat exchanger portion (32) and a convection heat ex...
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WO/2011/157418 |
The present invention relates to a gas turbine combustion chamber arrangement having an annular combustion chamber (1), having a diffuser element (2) which is arranged upstream of the annular combustion chamber (1) in the flow direction ...
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WO/2011/156078 |
A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the co...
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WO/2011/149973 |
A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annu...
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WO/2011/137110 |
Tuning processes implemented by an auto- tune controller (150) are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process...
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WO/2011/136834 |
Embodiments of the present invention include a unique gas turbine engine and a unique dome panel assembly for a gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations fo...
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WO/2011/134706 |
The invention relates to a burner system comprising at least two adjacent burners (7) that are separate from each other, each of which has at least one combustion chamber (6) and a head end (51), wherein the latter comprises at least a f...
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WO/2011/132426 |
A fuel distributor provided in a fuel supply device for a gas turbine engine has a moving body that moves in response to the fuel pressure in a fuel inlet, opens only a pilot port when the fuel pressure in the fuel inlet is lower than a ...
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WO/2011/128179 |
The invention relates to a swirl generator (1) for a torch (2), comprising a hub (3), an outer bounding wall (4), surrounding the hub (3), and a number of swirl vanes (5), which are arranged between the hub (3) and the outer bounding wal...
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WO/2011/130002 |
A splitter (148) is provided for improving a pressure recovery of a compressor discharge casing (CDC) (114) of a gas turbine engine. The CDC includes an annular wall (142) that extends generally axially along at least a portion of the CD...
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WO/2011/130001 |
A combustion liner assembly for a gas turbine includes an outer liner, the outer liner having a flange at a forward end. An inner liner is disposed within the outer liner. The inner liner has a first inner wall. A venturi includes a seco...
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WO/2011/128158 |
It is described a resonator device (101, 301) for damping a pressure oscillation within a combustion chamber (330), the resonator device comprising: a container (102, 302) filled with a gas; an opening (106, 306) in the container; and a ...
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WO/2011/129287 |
Disclosed is a gas turbine control device which can maintain stable combustion and good exhaust gas characteristics even if the catalyst is degraded. The disclosed gas turbine control device (6) is provided with a combustion device (2) w...
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WO/2011/121831 |
A combustor is provided with: nozzles which are arranged around the center axis of the combustor and which each have a base end connected to an oil supply pipe; a nozzle pipe base which supports the nozzles and which has an oil chamber f...
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WO/2011/117533 |
The invention relates to an annular combustion chamber for a turbomachine, comprising an external wall (2), an internal wall (3) and a chamber base (4) on which identical injection systems (5) are mounted along at least one ring, said in...
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WO/2011/118131 |
Provided is a film cooling structure which prevents a cooling medium film from being stripped off from a wall surface and increases the efficiency of the film on the wall surface, thereby allowing the wall surface to be efficiently coole...
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WO/2011/117395 |
The invention relates to a component (14) having an outer wall (25, 60) which can be exposed to a hot gas (15, 62) of a gas turbine, comprising a main body (32, 52), a duct (26, 28, 30, 54) provided for cooling the outer wall (25, 60) an...
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WO/2011/117042 |
Burner for stabilizing the combustion of a gas turbine. The invention concerns a burner for stabilizing the combustion of a gas turbine, which comprises a combustion chamber (5) and a number of nozzles opening out into the combustion cha...
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WO/2011/118210 |
Disclosed is a fuel supply device of a gas turbine engine, wherein a fuel distributor (66) has a fuel inlet (E1) through which fuel is introduced from a composite fuel passage (63), a pilot port (76) connected to a pilot fuel passage (64...
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WO/2011/118372 |
Provided is a lean-fuel intake gas turbine which has no pressure loss in the exhaust gas line that may lead to a drop in engine output and can be reduced in size of the gas turbine. The lean-fuel intake gas turbine includes a compressor ...
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WO/2011/117543 |
Annular combustion chamber for a turbomachine, comprising an external wall (11) and an internal wall (12) which are oriented substantially axially relative to the rotation axis of the turbomachine, said combustion chamber being closed up...
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WO/2011/110170 |
For a telemetry arrangement for transferring data from a rotating component, the telemetry rotor (13) connected to the rotating component comprises a front and a rear rotor part (13b, 13a), which are detachably joined to each other by me...
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WO/2011/107132 |
A device serves for providing hot exhaust gases for driving a turbine (24). The device has a burner (17), the combustion zone (23) of which is integrated directly on or in the gas inlet (turbine casing 29) of the turbine (24). The burner...
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WO/2011/104068 |
Disclosed is a gas turbine fuel injector and swirler assembly (58), comprising: a delivery tube structure (44) arranged on a central axis of the fuel injector and swirler assembly (58), a first fuel supply channel (43) arranged in the de...
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WO/2011/104304 |
The invention relates to system for injecting air and fuel (62) for the bottom of an annular combustion chamber of a turbine engine, including a central injector (26) and a peripheral annular fuel injector (43) including at least one fue...
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WO/2011/104304 |
The invention relates to system for injecting air and fuel (62) for the bottom of an annular combustion chamber of a turbine engine, including a central injector (26) and a peripheral annular fuel injector (43) including at least one fue...
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WO/2011/100019 |
Coating system for reducing CMAS infiltration of substrates includes at least an inner ceramic layer and an outer alumina-containing layer. The outer layer includes up to 50 percent by weight titania. Additional ceramic layers and alumin...
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WO/2011/096197 |
A fuel supply device for a gas turbine engine is provided with a fuel distributor (66) for distributing fuel, which is delivered from a collective fuel path (63), to a pilot fuel path (64) and a main fuel path (65). The fuel distributor ...
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WO/2011/092779 |
Disclosed is a gas turbine combustor (1) equipped with a fuel injection valve (13) that injects fuel (F) towards a combustion chamber (11), a swirler (14) that, in the vicinity of the fuel injection valve (13), takes in and circulates co...
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WO/2011/094682 |
A telemetry system for use in a combustion turbine engine (10) having a compressor (12), a combustor and a turbine (16) that includes a sensor (306) in connection with a turbine blade (301) or vane (22). A telemetry transmitter circuit (...
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WO/2011/094679 |
A telemetry system for use in a combustion turbine engine (10) that includes a first sensor (306) in connection with a turbine blade (301) or vane (22). A first telemetry transmitter circuit (312) is affixed to the turbine blade and rout...
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WO/2011/086320 |
The invention relates to a combustion chamber (100), in particular of a turboshaft engine, having an inner annular wall (102), an outer annular wall (104), and an annular chamber bottom (106) extending around an axis, the chamber bottom ...
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WO/2011/086336 |
The invention relates to a low-cost combustion-chamber injector device that has sturdier construction and is safer for use. For said purpose, the invention proposes configuring the parts specifically such as to be nested, in order to dis...
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WO/2011/084782 |
The combustor (10) includes an axially symmetric tube (12) along with means for introducing fuel (18) and air (20) into the tube. A swirler (24) is disposed within the tube to impart rotation in a first direction to the air/fuel mixture....
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WO/2011/080433 |
The infunnelion relates to the combustion chamber of a turbine engine, comprising at least one spark plug (11) borne by an outer casing and extending inside guiding means (14) borne by a rotating wall (3) of the chamber, said guiding mea...
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WO/2011/081770 |
A resonator system for a turbine engine can improve acoustic performance and cooling effectiveness. During engine operation, a combustor liner exhibits alternating hot and cold regions in the circumferential direction corresponding to th...
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WO/2011/080433 |
The infunnelion relates to the combustion chamber of a turbine engine, comprising at least one spark plug (11) borne by an outer casing and extending inside guiding means (14) borne by a rotating wall (3) of the chamber, said guiding mea...
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WO/2011/078972 |
Methods for providing a coating system for reducing CMAS infiltration of substrates exposed to hot and harsh climates Exemplar)' methods include optionally disposing a bond coat on a substrate, disposing an inner ceramic layer over the b...
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WO/2011/073075 |
Systems and methods provide for wear reduction in a combustion system of a gas turbine. A system for wear reduction includes: at least one substantially H-shaped block ( 202 ), the substantially H-shaped block ( 202 ) being configured to...
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WO/2011/073075 |
Systems and methods provide for wear reduction in a combustion system of a gas turbine. A system for wear reduction includes: at least one substantially H-shaped block, the substantially H-shaped block being configured to secure a transi...
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