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Matches 451 - 500 out of 8,554

Document Document Title
WO/2014/008053A1
A disclosed fuel injector provides mixing of fuel with airflow by surrounding a swirled fuel flow with first and second swirled airflows that ensures mixing prior to or upon entering the combustion chamber. Fuel tubes produce a central f...  
WO/2014/005921A1
The invention relates to a method for producing water from the exhaust stream (22) of a gas turbine system (100), characterized by the following steps: - feeding at least a portion of an exhaust stream (22) from the gas turbine system (1...  
WO/2014/004825A1
A catcher for a gas turbine engine includes a central hub, a plurality of struts, and a first ring. The plurality of struts are connected to and extend outward from the central hub. The first ring is connected to a mid-section of the plu...  
WO/2014/001230A1
The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially comprises at least one compressor, a first combustor which i...  
WO/2014/004266A1
A thrust reverser system for a gas turbine engine includes a duct including a cowling movable between an open position and a closed position in a direction transverse to a centerline of the gas turbine engine. The thrust reverser is supp...  
WO/2013/192540A1
A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench ...  
WO/2013/191937A1
A compressor housing (16) for a turbocharger with a recirculation cavity (60) formed between a volute base portion (40), an inducer (44) and an inlet section (46) to bleed airflow from a compressor impeller (14) back into the inlet secti...  
WO/2013/192523A1
A gas fuel turbine engine (100) may include a gaseous pilot fuel supply, a first main fuel supply, and a second main fuel supply. The first main fuel supply may provide gaseous fuel to a first plurality of fuel injectors (30), and the se...  
WO/2013/191877A1
An airfoil includes an airfoil body that extends between a leading edge and a trailing edge, a suction side and a pressure side, and a first end and a second end. At least one fitting is located on at least one of the first end and the s...  
WO/2013/191954A1
A method for operating a turbine engine (100) having a plurality of fuel injectors (30) arranged circumferentially in a combustor (50), with each fuel injector having a main fuel supply and a pilot fuel supply, includes supplying fuel to...  
WO/2013/189470A1
A combustion engine contains a mechanical rotor (4, 7) comprising at least one working tube (6) that is branched or unbranched, for supplying fuel into the mechanical rotor (4, 7), passing fuel through the working tube (6) and exhausting...  
WO/2013/188641A4
Systems and methods are provided for combined cycle power generation while reducing or mitigating emissions during power generation. Recycled exhaust gas from a power generation combustion reaction can be separated using a swing adsorpti...  
WO/2013/187944A3
A compressor section includes a counter rotating low pressure compressor that includes outer and inner compressor blades interspersed with one another and are configured to rotate in an opposite direction than one another about an axis o...  
WO/2013/188641A3
Systems and methods are provided for combined cycle power generation while reducing or mitigating emissions during power generation. Recycled exhaust gas from a power generation combustion reaction can be separated using a swing adsorpti...  
WO/2013/187944A2
A compressor section includes a counter rotating low pressure compressor that includes outer and inner compressor blades interspersed with one another and are configured to rotate in an opposite direction than one another about an axis o...  
WO/2013/184495A2
A shell for a combustor liner includes a cold side, a hot side, a row of cooling holes and a jet wall. The jet wall projects from the hot side for creating a wall shear jet of increased velocity cooling flow in a tangential direction awa...  
WO/2013/184619A1
A gas turbine engine is provided, which includes a first compressor rotor coupled to a first shaft, a second compressor rotor downstream of the first compressor and coupled to a second shaft. A combustor is disposed downstream of the com...  
WO/2013/184502A1
A heat shield for a combustor liner includes first linear film cooling slots through the heat shield and second linear film cooling slots through the heat shield. The first linear film cooling slots are run in a row and each of the first...  
WO/2013/184496A1
A combustor liner includes a heat shield, a shell, a series of trip strips, and a series of projecting walls. The heat shield has a shield cold side. The shell is attached to the heat shield and includes a shell hot side facing the shiel...  
WO/2013/184454A1
A seal land for a gas turbine engine can include a seal body that can extend between a leading edge portion, a trailing edge portion, a radially outer surface and a radially inner surface. A notch can extend at least partially through th...  
WO/2013/184504A1
A combustor liner is arcuate in shape and defines an axis and a circumferential direction. The combustor liner includes a first row of dilution openings and a second row of dilution openings. The first row runs in the circumferential dir...  
WO/2013/184495A3
A shell for a combustor liner includes a cold side, a hot side, a row of cooling holes and a jet wall. The jet wall projects from the hot side for creating a wall shear jet of increased velocity cooling flow in a tangential direction awa...  
WO/2013/184330A1
A latch assembly for securing a nacelle portion of a gas turbine engine includes first and second nacelle flow structures that define a portion of a bypass flowpath. A seal is engageable between the first and second nacelle flow structur...  
WO/2013/184329A1
A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream ...  
WO/2013/180895A1
An exemplary containment structure includes an annular wall configured to receive a rotatable portion of a turbomachine. A plurality of apertures extend radially through the annular wall. The apertures have a varying circumferential width.  
WO/2013/180917A1
A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compress...  
WO/2013/180424A1
The present invention relates to an apparatus for a fuel-air mixture using a rotary injection device and a gas turbine burner mounting the same, which as being applied to both cylindrical and annular burners includes a rotary injection d...  
WO/2013/179301A3
A gas turbine comprises a conveyor belt (2) converted into bladed rotor, a rotor cover (8, 9) secure to the rotor tightly, an evacuation means (11) to remove exhaust gas and a valve (5) to prevent back flow of gas which tends to cause op...  
WO/2013/176709A2
A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The in...  
WO/2013/176876A1
Disclosed is a liquid-gas mixer including a central passageway provided about an injector axis, and first and second gas passageways. The first gas passageway is radially outward of the central passageway and radially inward of the secon...  
WO/2013/176709A3
A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The in...  
WO/2013/177030A1
A method and device for modifying a gas turbine engine (100) is disclosed herein. The method for modifying a gas turbine engine (100) includes accessing a first outward end (717) of a first tube (713, 715) installed in the gas turbine en...  
WO/2013/172906A2
A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set o...  
WO/2013/173006A1
A method for making a component for a gas turbine engine comprises forming a non-metal substrate having at least one metal receiving surface. A cathode is formed corresponding to a shape of the at least one metal receiving surface. The c...  
WO/2013/172906A3
A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set o...  
WO/2013/172902A1
A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communic...  
WO/2013/167636A1
The invention relates to a method and system for retrofitting an aircraft in particular for driving a cryogenic fuel pump of aircraft engines. One of the problems of operating a drive of a cryogenic fuel pump is its high electric energy ...  
WO/2013/167638A1
The invention relates to a system for supplying a pump with cryogenic liquid, in particular, as fuel for an aircraft. Preferably a liquid gas such as liquid natural gas (LNG) is used as cryogenic fuel. During the suction of cryogenic liq...  
WO/2013/167639A1
The invention relates to a dispensing device for cryogenic liquids, in particular for fueling an aircraft, and to a vehicle which is equipped with a dispensing device for cryogenic liquids. During the intake of a cryogenic liquid into a ...  
WO/2013/167328A1
The invention relates to a rotor (3) for a turbomachine, wherein the rotor (3) comprises a planetary gear (1) on which low-pressure end stage blades (17) are arranged, wherein the planetary gear (1) is designed in such a way that the fre...  
WO/2013/165769A1
A geared architecture for a gas turbine engine includes a lubricant manifold for directing lubricant flow to the geared architecture. The manifold including annular channel and a bowl member received within the annular channel for defini...  
WO/2013/166084A1
A gas turbine afterburner includes a gutter electrode that helps to hold an afterburner flame. A charge source applies a majority charge to be carried by a turbine exhaust gas. Electrical attraction between the majority charge and the gu...  
WO/2013/165495A2
A method of measuring creep strain in a gas turbine engine (100) component, where at least a portion of the component has a material (84) disposed thereon, and where the material (84) has a plurality of markings (86) arranged in a visual...  
WO/2013/165495A3
A method of measuring creep strain in a gas turbine engine (100) component, where at least a portion of the component has a material (84) disposed thereon, and where the material (84) has a plurality of markings (86) arranged in a visual...  
WO/2013/165771A1
A disclosed gas turbine engine includes a core engine defined about an engine centerline axis, the core engine including a compressor section driven through a shaft by a turbine section. A core nacelle surrounds the core engine and a fan...  
WO/2013/165960A1
Systems and methods for gasifying a feedstock are provided. A feedstock can be introduced to a riser. A first oxidant can be introduced to a first mixing zone within the riser, thereby generating a first high temperature zone within the ...  
WO/2013/165868A1
A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shel...  
WO/2013/166284A1
A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defi...  
WO/2013/162887A1
An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and...  
WO/2013/163045A1
A method includes generating an exhaust gas from combustion gases with a turbine; recirculating the exhaust gas along an exhaust recirculation flow path; reducing moisture within the exhaust gas along the exhaust recirculation path with ...  

Matches 451 - 500 out of 8,554