Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 401 - 450 out of 8,616

Document Document Title
WO/2014/071065A3
A system includes a turbine combustor (160), which includes a first wall (264) disposed about a combustion chamber (262), a second wall (266) disposed about the first wall (264), and a third wall (268) disposed about the second wall (266...  
WO/2014/071136A3
A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber...  
WO/2014/071063A1
A system includes a turbine combustor (150) that includes a head end portion (166) having a head end chamber, a combustion portion (168) having a combustion chamber disposed downstream from the head end chamber, a cap (331) disposed betw...  
WO/2014/068344A4
The present invention relates to the method and structural configuration for environmentally safe waste and biomass processing to increase the efficiency of energy and heat generation. In the structural configuration of the invention sol...  
WO/2014/071088A1
A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products, a turbine section having one or more turbine stages between an upstream end and a downstre...  
WO/2014/071120A3
A system including a turbine combustor (160) with a head end portion (166) having a head end chamber, a combustion portion (168) having a combustion chamber disposed downstream from the head end chamber, a cap (331) disposed between the ...  
WO/2014/070279A2
An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between ...  
WO/2014/069409A1
This power generation system is provided with: a gas turbine (11) having a compressor (21), a combustor (22) and a turbine (23); a first compressed air supply line (26) that supplies compressed air, which has been compressed by the compr...  
WO/2014/071037A3
A system includes a gas turbine system having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine. The exhaust gas compressor is configured to compr...  
WO/2014/071089A1
In one embodiment, a system includes at least one sensor configured to communicate a signal representative of a gas turbine operations. The system further includes a controller communicatively coupled to the sensor. The system additional...  
WO/2014/071121A1
A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber...  
WO/2014/065185A1
A power generation system having a gas turbine engine that utilizes sunlight is provided with: a compressor (1) for compressing air (A), which is the working medium; a solar heater (3) for heating the air compressed by the compressor usi...  
WO/2014/060758A1
A heat engine (10) comprising: a feeder stage (20) comprising: a first compressor (24) for compressing first gas received at pressure P1 from a gas source to an elevated pressure and temperature; a reactor (28) for receiving gas compress...  
WO/2014/062220A1
A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide van...  
WO/2014/062367A3
A system and methods for increasing a combustibility of a low BTU natural gas are provided herein. The method includes increasing the adiabatic flame temperature of the low BTU natural gas using heavy hydrocarbons, wherein the heavy hydr...  
WO/2014/058463A1
A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid comm...  
WO/2014/058466A1
A gas turbine engine has a compressor section, a compressor case substantially surrounding the compressor section, and a diffuser case attached at an attachment interface to the compressor case. The attachment interface is between a forw...  
WO/2014/058455A1
A bearing support bracket for supporting the bearing assembly includes individually adjustable features for defining and enabling a desired stiffness.  
WO/2014/055110A1
A static guide vane for use in a fan section of a gas turbine engine includes an outer platform and an inner platform. The inner and outer platforms are connected by an airfoil. The airfoil have channels extending into a main body of the...  
WO/2014/055104A1
A gas turbine engine design process includes the steps of determining the location of a hot streak downstream of a combustor nozzle, and determining whether it would be most beneficial to have the hot streak initially impact a pressure s...  
WO/2014/055122A1
A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first ...  
WO/2014/055113A9
A gas turbine engine includes a fan rotating structure including a plurality of fan blades supported on a hub that defines a frontal area. A turbine section drives the fan through a geared architecture about the axis. The fan rotating st...  
WO/2014/055113A1
A gas turbine engine includes a fan rotating structure including a plurality of fan blades supported on a hub that defines a frontal area. A turbine section drives the fan through a geared architecture about the axis. The fan rotating st...  
WO/2014/055106A1
A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a bleed system that is configured to receive bleed air f...  
WO/2014/051688A1
A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an airfoil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades an...  
WO/2014/047685A1
The invention provides methods of generating electric power from underground coal seams with capture of carbon dioxide.  
WO/2014/052007A1
A mid-turbine frame (MTF) system for a gas turbine engine is disclosed. The MTF includes an inner case, an outer case and a fairing sandwiched between the inner and outer cases. The fairing includes an inner ring spaced apart from and co...  
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 ...  

Matches 401 - 450 out of 8,616