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Matches 451 - 500 out of 8,497

Document Document Title
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 ...  
WO/2013/160161A3
The invention relates to a gas and steam turbine plant (1) having a heat recovery steam generator (11) which is connected, at the flue gas side, downstream of a gas turbine (2) and having a low-temperature heat circuit (20) into which a ...  
WO/2013/162752A1
A thermal management system for a gas turbine engine includes a high pressure compressor rotor having a plurality of disks and a shaft; at least one forward cavity formed between a rim of at least one of the disks and the shaft and at le...  
WO/2013/156611A1
The invention relates to a system for generating and storing excess energy from renewable power sources in the form of hydrocarbons, which can be used in a closed circuit to produce electricity in an environmentally friendly manner again...  
WO/2013/158179A2
An example method of controlling performance of gearbox of a gas turbine engine includes establishing a gear characteristic of a plurality of double helical gears each disposed about a respective axis in a gearbox. Performance of the plu...  
WO/2013/158191A1
A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the ...  
WO/2013/154648A1
A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same par...  
WO/2013/155214A1
A system includes a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor. The exhaust compressor is configured to compress and route an exhaust gas from the turbine to the t...  
WO/2013/155491A1
An apparatus comprises an expander comprising a member moveable within a chamber in response to an expanding gas. A linkage is in communication with the member and configured to transmit out of the chamber, a power of the expanding gas. ...  
WO/2013/151162A1
A gas turbine combustor (12) is provided with a casing chamber (48), a combustor inner tube (42), a pilot combustion burner (44), main combustion burners (45) disposed so as to surround the pilot combustion burner (44), a fuel supply lin...  
WO/2013/150198A1
The present invention relates to a device (20) for sealing between the coaxial shafts of a turbomachine comprising an annular seal (23) able to perform sealing by contact with the outer shaft (12), said device being characterized in that...  
WO/2013/148503A8
An integrated process for the partial oxidation of whole crude oil mixed with a low cost finely divided solid ash-producing material in a membrane wall gasification reactor produces a syngas and, optionally, a more hydrogen-rich product ...  
WO/2013/148419A1
A fan drive gear system for a gas turbine engine includes a carrier that supports circumferentially arranged gears. A torque frame has circumferentially arranged fingers with each finger including a bore having a bore axis. A bushing is ...  
WO/2013/149249A1
An air blocker ring assembly (40) includes a proximal end (49) and a distal end (50), a blocker ring (42) having a protrusion (60, 62, 64), and a blocker ring support (44). The blocker ring support having a wall portion (108, 94, 96), th...  
WO/2013/148503A1
An integrated process for the partial oxidation of whole crude oil mixed with a low cost finely divided solid ash-producing material in a membrane wall gasification reactor produces a syngas and, optionally, a more hydrogen-rich product ...  
WO/2013/144006A3
The invention relates to a combined cycle power plant (10a) comprising a gas turbine (11a,b) the exhaust gas outlet of which is connected to a heat recovery steam generator (19), which is part of a water/steam cycle (35), whereby, for ha...  
WO/2013/142941A1
The invention relates to continuous-combustion open-layout gas-turbine engines, and can be used in transport plants, for example, in aviation plants and in power-generating plants, and also as a drive in gas-pumping units. An at least tw...  
WO/2013/143827A3
The invention discloses a method for operating a combined cycle power plant (10) with an integrated CO2 capture unit (14), wherein flue gas of a gas turbine (11) is led along an flue gas path through a heat recovery steam generator (19),...  
WO/2013/144839A1
The present invention relates to a thermochemical and thermodynamic cycle which can be executed by a thermal propulsion machine, such as a reciprocating engine, a rotary engine or a gas turbine, and which is adapted to attain high energe...  
WO/2013/147977A1
An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the s...  
WO/2013/148445A1
A rotor includes a disk that has slots circumferentially arranged around its periphery. Blades include respective roots that are mounted in respective ones of the slots. The roots are smaller than the slots such that there are circumfere...  
WO/2013/143975A1
The invention relates to a method for operating a gas turbine (6) which comprises a compressor (1) with annular inlet area, at least two burners, a combustion chamber (4, 14, 15) and a turbine (7, 16, 17). According to the method, at lea...  

Matches 451 - 500 out of 8,497