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WO/2014/200588A2 |
A combustor of a gas turbine engine includes an additively manufactured liner panel with a heat transfer augmentation feature.
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WO/2014/197045A2 |
A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.
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WO/2014/188121A1 |
The invention relates to an aircraft turbopropeller (10) comprising two coaxial contra-rotating unducted propellers (12, 14'), upstream and downstream respectively, each propeller comprising an annular row of blades. The blades of the do...
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WO/2014/189542A1 |
An on-board Flex-Fuel H2 Generator provides devices and the methods of operating these devices to produce H2 and CO from hydrocarbons and bio-fuels. One or more parallel autothermal reformers are used to convert the fuels into H2 over th...
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WO/2014/189593A2 |
One example of a gas turbine engine can include a first compressor and a first turbine connected to the first compressor by a first shaft. The engine can include a reheat combustor, which is disposed downstream of the first turbine, and ...
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WO/2014/189694A1 |
A turbomachine assembly (102) has a compressor section (202) including a first end (208) of a rotating member (206) and a first cover (218) configured to substantially enclose the first end therein. The compressor section includes a bypa...
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WO/2014/183651A1 |
An aircraft pipeline wheel gas engine is provided with a rotary pipeline burning power wheel (17). The burning power wheel (17) is formed by a burning power wheel disc (18) and a flame gas pipe (20). The burning power wheel disc (18) is ...
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WO/2014/186146A1 |
A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body sp...
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WO/2014/186149A1 |
An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection port...
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WO/2014/186148A1 |
A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from th...
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WO/2014/186150A1 |
A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an ...
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WO/2014/177836A1 |
In a gas turbine engine, the booster compressor is driven by both the low pressure or fan shaft and high pressure shaft through a differential gear arrangement. The rotational speed of the booster compressor is intermediate between the s...
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WO/2014/175405A1 |
This IGCC plant is provided with an ASU which separates oxygen gas and nitrogen gas from air, a coal gasification furnace which uses an oxidizing agent to gasify coal, and a gas turbine which is driven by the combustion gas resulting fro...
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WO/2014/175404A1 |
This IGCC plant is provided with a coal gasification furnace which uses an oxidizing agent to gasify coal, a gas turbine which is driven by the combustion gas resulting from burning a fuel gas obtained by refining, in gas refining equipm...
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WO/2014/170600A1 |
A nozzle (7) for an aircraft turboprop engine with an unducted fan, comprising: -an inner wall (15), -an outer wall (17) set radially apart from said inner wall, -a junction area (27) of said inner and outer walls comprising at least one...
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WO/2014/165161A1 |
A fluid plenum including a body defining an internal cavity having an inlet and an outlet. The fluid plenum further includes at least one wall positioned in the internal cavity that divides the internal cavity into first and second passa...
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WO/2014/163887A1 |
A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or ...
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WO/2014/163709A2 |
The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage a portion of an airfoil of each turbine ...
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WO/2014/156277A1 |
An intake air cooling device (100) is configured so as to uniformly spray water into intake air even during partial operation. The intake air cooling device (100) is provided on the rear-stage side of a pre-filter (24) provided on the in...
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WO/2014/149099A1 |
A gas turbine engine includes a centrifugal compressor having an improved impeller structure. The impeller structure includes a near axial discharge configuration thus reducing the overall size of the envelop surrounding the compressor a...
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WO/2014/152875A1 |
A gas turbine engine includes an inner annular combustor radially inboard of an outer annular combustor. An outer variable turbine vane array is downstream of the outer annular combustor and an inner variable turbine vane array downstrea...
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WO/2014/151656A1 |
The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbi...
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WO/2014/141830A1 |
Provided is a fuel spray nozzle provided with: a liquid fuel channel (15) which is a channel for liquid fuel; a liquid fuel injection hole (19) which is a hole for communicating the liquid fuel channel (15) and the inside of a combustion...
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WO/2014/137456A1 |
One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of noz...
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WO/2014/137435A2 |
An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assem...
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WO/2014/137452A1 |
A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatab...
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WO/2014/133499A2 |
Systems and methods for passive thermal management of foil bearing systems are disclosed herein. The flow of the hydrodynamic film across the surface of bearing compliant foils may be disrupted to provide passive cooling and to improve t...
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WO/2014/133616A1 |
A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembl...
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WO/2014/130027A1 |
Contemplated configurations and methods are presented for effectively controlling the temperature in an oxy-fuel combustion system. Contemplated systems preferably introduce water independent of the fuel and oxygen into the combustion ch...
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WO/2014/128124A1 |
The invention refers to a method for operating a gas turbine plant. According to the method a first fuel gas (5) with a first fuel reactivity and a second fuel gas (14) with a second fuel reactivity which is higher than the first fuel re...
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WO/2014/127922A1 |
Power station (1) having a gas turbine (2), having an exhaust gas line (3) of the gas turbine (2) and having a precipitation device (4) for carbon dioxide, wherein the precipitation device (4) comprises an absorption device (5) which is ...
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WO/2014/126236A1 |
The present invention is equipped with; a waste heat recovery device (100) that uses heat from exhaust gas (EG) exhausted from a gas turbine (10) to generate steam; and a purified water generation device (200) that uses the energy of the...
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WO/2014/126190A1 |
A fuel gas calorie estimation device equipped with: a fuel gas flow volume acquisition unit that acquires the flow volume of a fuel gas flowing into the combustor of a gas turbine; a state quantity acquisition unit that acquires the stat...
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WO/2014/124161A1 |
A system includes a turbine combustor, a turbine, an exhaust gas compressor, a flow path, and at least one catalytic converter. The turbine is driven by combustion products from the turbine combustor. The exhaust compressor is configured...
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WO/2014/124291A1 |
A turbocharger for use with an internal combustion engine is provided. The turbocharger comprises a differential device (204) having a carrier portion (226), a compressor portion (212), and a turbine portion (210). The compressor portion...
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WO/2014/113372A1 |
A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the f...
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WO/2014/109788A1 |
A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.
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WO/2014/109786A1 |
In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor ...
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WO/2014/110445A1 |
A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section,...
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WO/2014/105325A1 |
A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pum...
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WO/2014/105327A1 |
Turbine engine assemblies including a turbine engine assembly having a turbine core comprising a compressor section, a combustion section, a turbine section, and a nozzle section, which are axially aligned, wherein the combustion section...
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WO/2014/105328A1 |
A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels, including a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tan...
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WO/2014/104526A1 |
According to the present invention, a power generation system is a system for generating electric power, and comprises: a fuel cell system for enabling the supplied reactant to react so as to generate electric power; and a circulation sy...
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WO/2014/106265A2 |
A gas turbine system includes a combustor configured to combust an oxidant and a fuel in the presence of an exhaust gas diluent to produce combustion products, an oxidant supply path fluidly coupled to the combustor and configured to flo...
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WO/2014/105331A1 |
A turbine engine assembly (101) and dual fuel aircraft system having a cryogenic fuel system (500), having a cryogenic fuel reservoir (502), a vaporizer heat exchanger (504), a liquid supply line (506) operably coupling the fuel reservoi...
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WO/2014/102127A1 |
A drive system for driving a load (21) by means of a gas turbine (3). The gas turbine comprises a gas generator (5) having a gas-generator rotor (5R) and comprising at least one gas-generator compressor (9) and one high-pressure turbine ...
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WO/2014/105113A1 |
A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at leas...
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WO/2014/104969A1 |
A method for producing energy including: producing fuel gases from biomass raw material in a main receptacle unit (8), feeding produced fuel gas to a consumer unit (2,3), transferring energy from the consumer unit to at least one energy ...
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WO/2014/099364A1 |
A fuel system is disclosed. The fuel system may include a fuel supply, a fuel supply conduit fluidly connecting the fuel supply to an engine, and a fuel pump in fluid communication with the fuel supply conduit. The fuel system may also i...
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WO/2014/098524A1 |
According to one specific embodiment of the present invention, disclosed is a circulating fluidized bed gasifier which is capable of increasing a combustion region and providing an improved carbon conversion rate with a heat exchanger in...
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