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Patent Searching and Data


Matches 401 - 450 out of 8,556

Document Document Title
WO/2014/051690A1
A combustor assembly for a gas turbine engine includes a combustor shell, a TOBI, a case, and a joint for securing the combustor shell, TOBI and case together. The joint has a combustor flange integral to the combustor shell. A TOBI flan...  
WO/2014/044254A3
The invention relates to a system for producing hot water and/or steam having a high-temperature reservoir for use in a gas turbine power station, wherein the energy for charging is provided from at least one external energy source and/o...  
WO/2014/044254A4
The invention relates to a system for producing hot water and/or steam having a high-temperature reservoir for use in a gas turbine power station, wherein the energy for charging is provided from at least one external energy source and/o...  
WO/2014/043051A1
Provided herein is a method, device and installation for devolatizing a solid feedstock, comprising carbon-based waste selected from the group consisting of hazardous material, biomass, animal manure, tires, municipal solid waste and ref...  
WO/2014/037128A1
A gas turbine plant (1) comprising at least one gas turbine (10) with a compressor stage (11) and an expansion stage (12), an exhaust gas line (20) to guide the flow of exhaust gas exiting from the expansion stage (12) during operation o...  
WO/2014/039246A1
An industrial gas turbine engine (10) rated for at least 75 MW maximum output, including: a can annular combustion assembly (80); and a single rotor shaft (114); wherein a combustion section length (112) between a trailing edge (28) of a...  
WO/2014/039826A8
A gas turbine engine compressor spacer (230) includes a body (229) with a hollow cylinder shape. The body (229) includes an outer surface (232) with an axially forward end. The body (229) also includes a forward face (233) extending radi...  
WO/2014/039247A1
An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along...  
WO/2014/039826A1
A gas turbine engine compressor spacer (230) includes a body (229) with a hollow cylinder shape. The body (229) includes an outer surface (232) with an axially forward end. The body (229) also includes a forward face (233) extending radi...  
WO/2014/032830A1
The present invention relates to the extension of the range of functions of a so-called IGCC-System (integrated gasification combined cycle system; combined process comprising integrated coal gasification) and a modified IGCC system. By ...  
WO/2014/031203A3
An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first ...  
WO/2014/031182A1
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low p...  
WO/2014/031197A2
An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The fan includes a first plurality of f...  
WO/2014/031197A3
An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The fan includes a first plurality of f...  
WO/2014/031203A2
An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first ...  
WO/2014/028348A2
A Low Cost Radial Gas Burner (LCRGB) burner comprises a gas turbulator means, at least one means for producing an ambient-air-inducing jet of the gaseous fuel to create a self-sustaining combustible fuel-air mixture, and a combustion ini...  
WO/2014/028085A2
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting th...  
WO/2014/028085A3
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting th...  
WO/2014/025441A2
gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first ex...  
WO/2014/025441A3
gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first ex...  
WO/2014/020772A1
The present invention is provided with: a high-pressure gas turbine (3H); a first rotating shaft (4H) connected to a compressor (1) and the high-pressure gas turbine; an electric motor (9) connected to the first rotating shaft (4H); a sp...  
WO/2014/022122A1
A gas turbine engine includes a core defining an engine central longitudinal axis. An inner-fixed structure is radially outward of the core. A core cowl extends from the inner-fixed structure to a trailing edge. A thrust reverser is spac...  
WO/2014/020236A1
An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is ...  
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...  

Matches 401 - 450 out of 8,556