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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...
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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...
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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 ...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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. ...
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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...
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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...
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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 ...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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WO/2013/144904A1 |
Disclosed herein is a system comprising an air reactor; where the air reactor is operative to oxidize metal oxide particles with oxygen from air to form oxidized metal oxide particles; a fuel reactor; where the fuel reactor is operative ...
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WO/2013/141930A1 |
A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
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WO/2013/139103A1 |
An isothermal compression type heat engine using air as a heat working medium, and an operating method thereof. The isothermal compression type heat engine comprises an isothermal air compressor (1), a combustion chamber (4), and an expa...
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WO/2013/139880A1 |
In a method for operating a gas turbine (11), NOx is removed from the exhaust gases of the gas turbine (11) by means of a selective catalysis device (14) with the addition of NH3. The method achieves an extremely low NOx content while si...
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WO/2013/141984A2 |
A chemical reactor comprises a flow channel, a source, and a destination. The flow channel is configured to house at least one catalytic reaction converting at least a portion of a first nanofluid entering the channel into a second nanof...
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WO/2013/135289A1 |
The invention relates to an energy converter (10) comprising a constant working volume (14) which is surrounded by a housing (12) and is divided by a heat exchanger arrangement (16) into a first constant working volume (18) and a second ...
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WO/2013/138215A1 |
An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging ai into a discharge manifold. The discharge manifold containin at le...
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WO/2013/138217A1 |
A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed.
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WO/2013/138041A1 |
An arrangement (100) for delivering combustions gas from a plurality of combustors onto a first row of turbine blades along respective straight gas flow paths, including: a hoop structure (104) at a downstream end of the arrangement and ...
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WO/2013/135580A1 |
An exhaust turbo pump of an internal combustion engine has multiple pairs of turbine and compressor wheels rotatable about a common axis, an inner pair of wheels being connected by a tubular shaft rotatable relative to a spindle connecti...
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WO/2013/138212A1 |
A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.
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WO/2013/137960A1 |
An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in...
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WO/2013/133935A1 |
A fuel heating system for a gas turbine engine comprises a first heat exchanger, a second heat exchanger, a fuel pump and a valve. The first heat exchanger produces a heated air flow. The second heat exchanger receives the heated air flo...
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WO/2013/132433A1 |
A method of operating a turbine unit, wherein recirculated exhaust gas is contacted with a cooling and absorption liquid in a packed bed. An exhaust gas treatment system for a turbine unit, wherein an exhaust gas recirculation line compr...
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WO/2013/133997A1 |
An erosion resistant and hydrophobic article includes a core that has a first hardness and a surface on the core. The surface includes a plurality of geometric features that have a second, greater hardness. The geometric features define ...
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WO/2013/130296A1 |
A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a driv...
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WO/2013/130148A1 |
A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configur...
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WO/2013/130290A1 |
A component blending tool assembly, includes a material removing surface that is moved to provide a blended area in a component, the material removing surface having a spherical contour mimicking a predetermined depth ratio of the blende...
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WO/2013/127878A1 |
Shaft arrangement in a turbomachine, in particular in an aircraft engine, characterized by a tie rod (1) which is configured substantially as a sleeve for axial bracing of a spur toothing system (2) which connects two parts of a first ho...
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WO/2013/127916A1 |
The invention relates to a method for operating a gas turbine (6), in which an oxygen-reduced gas (21) and fresh air (2) are delivered to a compressor (1) of the gas turbine (6) in a radially staged manner, the fresh air (2) being delive...
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WO/2013/130289A1 |
An example thrust reverser blocker door includes a blocker door that is movable from a stowed position to a deployed position. Flow moves through an area of a bypass flowpath when the blocker door is in the stowed position. The blocker d...
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WO/2013/130309A1 |
A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine secti...
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WO/2013/126728A1 |
A turbine engine exhaust nozzle includes a core gas duct, a nozzle duct, and a thrust vectoring duct system having a duct valve, a first vectoring duct and a second vectoring duct. The nozzle duct directs a first portion of core gas from...
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WO/2013/124997A1 |
Provided are a power generating apparatus, a power generating method, a decomposition-gas boiler, and a decomposition-gas turbine with which nitrous oxide can be used as an environmentally friendly energy source. A fuel gas including nit...
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WO/2013/126125A2 |
A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner ...
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WO/2013/121262A1 |
A solar power plant in a new split configuration of a solar Brayton cycle or Brayton/Rankine combined cycle which comprises an array of heliostat mounted mirrors, a solar receiver and a high pressure section of a Brayton cycle power plan...
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WO/2013/119645A1 |
A turbine engine shaft includes a first sub-shaft, a second sub-shaft and a tie shaft. A first bearing surface of the first sub-shaft axially engages a second bearing surface of the second sub-shaft. The tie shaft includes an intermediat...
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WO/2013/119520A1 |
A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, ...
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WO/2013/116023A1 |
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...
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WO/2013/116034A1 |
A method of managing a gas turbine engine operating line includes detecting an air speed and a fan speed. A data table is referenced that includes a desired variable area fan nozzle position based upon air speed and fan speed. The detect...
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