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Patent Searching and Data


Matches 401 - 450 out of 8,882

Document Document Title
WO/2014/186008A3
A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, a...  
WO/2015/009942A1
A fuel circulation system and methods are provided. The system includes a supply pump for providing an outlet flow of fuel. The system also includes at least a first and a second servo. The first servo is connected to an outlet of the su...  
WO/2015/010033A1
An engine fuel system and methods are provided. The engine fuel system includes a supply arrangement for providing an outlet flow of fuel to a bypass metering arrangement. The bypass metering arrangement in turn provides a metered flow o...  
WO/2015/009392A2
A turbine nozzle apparatus includes: a vane (16) extending between inner and outer bands (12, 14), the interior of the vane (16) being open and communicating with an aperture (30) in the outer band (14), wherein the vane (16) and the ban...  
WO/2014/106265A3
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...  
WO/2015/009931A1
A fuel pressure regulation system is provided. The fuel pressure regulation system includes a supply arrangement for supplying an outlet flow. A primary metering circuit is provided, an inlet of which receives a first portion of the outl...  
WO/2015/007501A1
A method of operating a turbine engine (10), the turbine engine (10) comprising an inlet (12), a shaft (22, 24), a turbine (28, 30), a control system (50), a fuel system (51) and a modular liquid fuel burner system (45) having at least t...  
WO/2014/188245A3
Provided is a turbine housing of a turbosupercharger provided in an exhaust passage of an internal combustion engine, in which the turbosupercharger has a turbine wheel provided in the exhaust passage, and an outlet of the turbine housin...  
WO/2015/006538A1
The present disclosure relates generally to the field of variable geometry guide vanes for gas turbine engines. More specifically, the present disclosure relates to a plastic variable inlet guide vane for a gas turbine engine.  
WO/2015/006005A1
In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the s...  
WO/2015/002716A1
A heating body for an electrically heated filter screen includes a heater element having an outer surface and a metallic protective layer having an inner surface. An insulating layer is disposed between the heater element outer surface a...  
WO/2015/002370A1
Disclosed is a liquid fuel vaporization system. The system according to the present invention comprises: a first turbine unit; a first waste heat recovery unit; and a fuel supplier. The first turbine unit generates a first electrical ene...  
WO/2015/002402A1
According to an aspect of the present invention, a gas turbine system is provided which comprises: a compression unit; a combustion unit inducing combustion by using first compressed air from the combustion unit; a turbine unit generatin...  
WO/2014/210079A1
A method of controlling an exhaust gas recirculation (EGR) gas turbine system includes adjusting an angle of a plurality of inlet guide vanes of an exhaust gas compressor of the EGR gas turbine system, wherein the plurality of inlet guid...  
WO/2014/210081A1
A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of...  
WO/2014/209454A1
A hybrid fuel airplane and methods are presented. A cryogenic fuel is transferred to an airplane propulsor from an airplane fuel system comprising a cryogenic fuel tank (302) and a jet fuel tank (310). The cryogenic fuel tank (302) confo...  
WO/2014/202881A1
The invention relates to a jet pump type ejector (36) for a turbomachine, including a duct (40) through which a secondary ventilation air flow passes, and a first end of which forms an air intake (42) and a second end of which forms an a...  
WO/2014/200582A1
A method and apparatus of using cryogenic fuel (12) in an engine (101) for an aircraft (5) wherein the cryogenic fuel (12) is supplied to the engine for combustion.  
WO/2014/200830A1
A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up pr...  
WO/2014/200597A2
Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to a shaft and a stator positioned adjacent ...  
WO/2014/196985A1
A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation ...  
WO/2014/133645A3
A gas turbine engine (50) is disclosed which includes a bypass passage (58) that in some embodiments is capable of being configured to act as a resonance space. The resonance space can be used to attenuate or accentuate a noise produced ...  
WO/2014/158307A3
A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a ...  
WO/2014/189568A2
An example section of a gas turbine engine includes a plurality of variable vanes circumferentially disposed about an engine axis, a first moveable annular ring disposed on an upstream side of the variable vanes, a second movable annular...  
WO/2014/189574A2
A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes abo...  
WO/2014/188245A2
Provided is a turbine housing of a turbosupercharger provided in an exhaust passage of an internal combustion engine, in which the turbosupercharger has a turbine wheel provided in the exhaust passage, and an outlet of the turbine housin...  
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...  
WO/2014/158237A3
A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes. One aspect is the ability to provide...  
WO/2014/158240A3
A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the h...  
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...  
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...  
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...  
WO/2014/130117A3
A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a fir...  
WO/2011/162960A3
The present techniques provide systems and methods for recovering energy from flare gases in chemical plants and refineries. The systems use an engine to burn a portion of gas diverted from the flare system. The engine may be a reciproca...  
WO/2014/182616A2
Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady s...  
WO/2014/182507A1
A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The bloc...  
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...  
WO/2014/174208A1
The method according to the invention comprises, during a phase (EO) of starting up the turbomachine : — a step (E10) of open-loop generation of a control (WF_OL) of the flow of fuel based on at least one pre-established law; and — a...  
WO/2014/170058A1
The present invention relates to a method for providing negative control power for an electrical supply and/or transmission network by means of the operation of a gas turbine (1), comprising the following steps: a dynamo-electric machine...  
WO/2014/166671A1
A method for reducing the CO emissions of a gas turbine (1), having a compressor (6), having a turbine (10) and having an air preheater (22) positioned upstream of the compressor (6), is intended to permit technically simpler regulation ...  
WO/2014/116326A3
A method of establishing a boundary for a material improvement process on a workpiece is disclosed. The method may include identifying a maximum allowable damage depth on the workpiece; identifying a maximum constant thickness line on th...  
WO/2014/113105A3
A fuel nozzle for a combustor of a gas turbine engine, includes a swirler tip along an axis; and a helical adapter along the axis and within the swirler tip. A method of directing a fuel gas and a liquid through a fuel nozzle and into a ...  
WO/2014/161661A1
The invention relates to a method for operating an internal combustion engine in a combined heat and power generation system (1) and to a combined heat and power generation system (1) comprising an internal combustion engine of this type...  
WO/2014/165364A1
A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes ...  
WO/2014/158307A2
A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a ...  
WO/2014/158335A1
A system includes a controller configured to control an operational behavior of a turbine system. The controller includes a droop response system configured to detect one or more operational characteristics of the turbine system as an in...  
WO/2014/158238A1
Control systems and methods for an aircraft propulsion system are disclosed in which the propulsion control system (140) is integrated to intelligently control aircraft propulsion and minimize transient effects from the power demands of ...  
WO/2014/159504A1
A bleed valve assembly according to an exemplary aspect of the present disclosure includes, among other things, a bleed adaptor having an inlet portion, a fitting opposite the inlet portion, an adaptor body that extends between the inlet...  
WO/2014/158455A1
An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and t...  
WO/2014/150377A1
A system and method for implementing stage-by-stage counter rotation in a multi-stage axial compressor of a gas turbine engine. The system includes an electrical power generator and an electric motor (2). A turbine-driven shaft (3) conne...  

Matches 401 - 450 out of 8,882