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Patent Searching and Data


Matches 451 - 500 out of 8,618

Document Document Title
WO/2014/018382A1
A gas turbine engine comprises a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case, a shaft rotatable relative to the fan case about an engine center axis, and a geared architecture ...  
WO/2014/018141A3
A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compre...  
WO/2014/018385A1
An exhaust duct for a gas turbine engine has an inner wall and an outer wall connected by a plurality of spaced ribs. The duct extends axially. The ribs extend circumferentially across an entire cross-section of the inner and outer walls...  
WO/2014/016498A1
The turbine engine (1) comprises a turbo compressor (2) of which the centrifugal compressor (61) and the turbo compressor turbine (62) are connected by a regeneration - combustion canal (34) which comprises a continuous combustion chambe...  
WO/2014/017217A1
A system for low-concentration-methane gas oxidation which is equipped with a single heat source device (GT) and an oxidation device (OD) for catalytically oxidizing a low-concentration methane gas using heat from the heat source device,...  
WO/2014/018199A1
A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a s...  
WO/2014/018141A2
A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compre...  
WO/2014/018963A1
A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which...  
WO/2014/018277A1
A bracket for an augmentor assembly of a gas turbine engine includes a first mount attachable to a support structure. A second mount is attachable to an augmentor pilot assembly and extends radially inward of the support structure. First...  
WO/2014/014773A1
A first stage compressor disk (221) of a gas turbine engine (100) includes a body (240). The body (240) includes a forward end (238), an aft end (239), and an outer surface (241). The body (240) also includes a plurality of forward balan...  
WO/2014/014550A1
A gas turbine engine component such as a laminate airfoil having a static pressure transducer and having a plurality of structural fiber layers bonded with a polymer matrix composite. The transducer includes a lattice formed from a plura...  
WO/2014/009524A1
Power plant (1) and method to operate such a power plant, the power plant comprising a gas turbine (2) and a heat recovery boiler arrangement (3). The gas turbine comprises a compressor inlet (18) with a fresh air intake sector (64) and ...  
WO/2014/011244A3
A Brayton cycle heat engine includes a compressor, a combustion chamber, and a turbine. The Brayton cycle heat engine also includes a heat exchanger positioned at least partially within the combustion chamber. The heat exchanger is confi...  
WO/2014/009511A1
The invention pertains a power plant (1) comprising a gas turbine (2), a heat recovery boiler arrangement (3) with at least a boiler inlet (10), and an outlet side with a first exit (13) connected to a stack (15) and a second exit (14) c...  
WO/2014/011405A1
A fuel-air premixer for a combustor of a gas turbine engine includes a central passage disposed along an axis and operable to communicate a first airflow and an outer annular passage about the axis operable to communicate a second airflo...  
WO/2014/011252A2
A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan.  
WO/2014/011379A1
A diaphragm assembly includes a cylinder, a circular flange, and a diaphragm. The cylinder defines an axis and includes a first end and a second end opposite the first end. The circular flange is coaxial with the cylinder and at a greate...  
WO/2014/007896A3
A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compre...  
WO/2014/008033A1
A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment cas...  
WO/2014/007897A3
A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compre...  
WO/2014/006297A1
The invention relates to a device (1) for simulating an ingestion of chunks of ice by an engine (2), comprising: - a main tank (10) forming a cavity for a fuel, and connected to an inlet of the engine (2) by a pipe (3), - an injection sy...  
WO/2014/007173A1
A wastewater treatment system and combined power generation equipment are provided with which wastewaters that are produced when a coal gasification gas is purified to obtain a purified gas are efficiently treated and the amount of the w...  
WO/2014/006564A1
A combustor of the type used for producing energy using biomass as fuel, wherein the combustor comprises at least one cyclonic and refractory combustion chamber, said combustion chamber being of a compact size, said combustor defines a m...  
WO/2014/007896A2
A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compre...  
WO/2014/008347A1
A fuel nozzle arrangement includes an annular combustor (14A - 14D)having four quadrants (Q1 - Q4). Fuel injectors are located in the four quadrants (Q1 - Q4) and each fuel injector has either a first or second type nozzle (40H, 40C) att...  
WO/2014/007908A1
An exhaust duct comprises a shroud body, a forward flange assembly, an aft flange assembly, an intermediate flange assembly, and a first plurality of bleed ports. The forward flange assembly extends radially inward from a forward shroud ...  
WO/2014/007880A3
A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The b...  
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...  

Matches 451 - 500 out of 8,618