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Patent Searching and Data


Matches 501 - 550 out of 8,852

Document Document Title
WO/2014/100667A1
A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.  
WO/2014/093279A1
A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor ...  
WO/2014/086541A1
Gas turbine fuel supply method and arrangement It is described a method of controlling a supply of a fuel to a combustor of a gas turbine comprising a compressor upstream of the combustor, the method comprising: supplying the fuel (105) ...  
WO/2014/088671A2
A gas turbine engine variable bleed apparatus (48) includes a variable bleed valve door (50) disposed in a bleed inlet (47) in a transition duct (29), rotatable about two or more separate pivot points (160), operable to open and close an...  
WO/2014/086540A1
It is described a method of controlling a supply of a fuel (105) to a combustor (101) of a gas turbine comprising a compressor upstream of the combustor, the method comprising: supplying the fuel (105) to the combustor (101); obtaining a...  
WO/2014/085292A1
A system for diagnosing a rotating airfoil has an image capture device and a light emitting device. A control is programmed to actuate at least one of the image capture device and the light at a particular time to capture an image of a r...  
WO/2014/080758A1
The present invention resolves trouble caused by a difference in the temperature of different types of fuel gas. A power generation system (10) for using exhaust fuel gas (L3) emitted from an SOFC (13) as the fuel for the combustor of a ...  
WO/2013/025818A9
An improved system for providing fuel uses a centrifugal pump arrangement that provides dual pressure. The dual pressure pump assembly includes a centrifugal pump for supplying pressurized fluid to an associated downstream use, and an au...  
WO/2014/076400A1
The invention concerns an aircraft turbomachine computer comprising a parallelepiped metal housing (10) containing an electronic circuit incorporating a control channel and a monitoring channel. The housing (10) of the invention comprise...  
WO/2014/078221A1
A gas turbine engine has a compressor, a fan for delivering air into the compressor and into a bypass duct, a combustion section and a turbine section. A control for the gas turbine engine is programmed to change a fueling level and posi...  
WO/2014/072619A1
The invention relates to a method and to a device for determining, in real time, the flow rate of air collected from an aircraft engine (39) by a system (1) for collecting air from the engine, comprising: acquisition means (33) for acqui...  
WO/2014/031199A3
A method of protecting operating margin of the gas turbine engine includes calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine that has a compressor section with variable vanes that are movable subject ...  
WO/2014/073059A1
The purpose of the present invention is to provide gas turbine power generation equipment capable of suppressing missteps when an instantaneous voltage drop or other grid accident has occurred, in a local grid having naturally fluctuatin...  
WO/2014/074371A1
A system for providing fuel to a combustor assembly in a gas turbine engine includes a main fuel valve assembly a plurality of multi-stage combustor valve assemblies. Each multi-stage combustor valve assembly is provided for delivering f...  
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/2014/070630A1
A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the sync...  
WO/2014/066276A2
Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical power demand.  
WO/2014/066210A1
A variable bleed valve (49) includes a variable bleed valve door (50) disposed in a bleed inlet (47) in transition duct (29) and rotatable about an axis (160) at or near a forward end (53) of door (50). Valve (49) is operable to open and...  
WO/2014/028093A3
An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots. The OD shroud is positioned radially outward from the ID ...  
WO/2014/058710A1
A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compress...  
WO/2014/059000A1
An engine monitor includes a first tuned modeling unit, a second tuned modeling unit and a monitoring unit. The first tuned modeling unit models dynamics of a first engine by processing first control data with a first engine model to pro...  
WO/2014/053421A1
The turboexpander and driven turbomachine system comprises: a turboexpander (13) configured for expanding a first fluid and comprising an expander stage with one ex- pander impeller; a first set of moveable inlet guide vanes (23) at the ...  
WO/2014/053752A1
The invention relates to a method for monitoring a thrust fault of a turbofan during a modification of the thrust setting (NCONS) of said turbofan, said method comprising a step of processing the thrust setting (NCONS) by means of a filt...  
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/2014/055124A1
A disclosed control system and method of controlling a gas turbine engine utilizes a thrust rating schedule generated from airframe selected requirements. The system utilizes a generic logic structure for ratings combined with simple sel...  
WO/2014/011304A3
A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side sur...  
WO/2014/055751A1
An air bleed system for a gas turbine engine includes an annular bleed case with a manifold therein. The annular bleed case has a forward section and an aft section and ligaments connecting the two sections. The forward section, the aft ...  
WO/2014/052269A1
An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement o...  
WO/2014/051678A1
A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to r...  
WO/2014/049260A1
The present invention relates to a method for differentiating control failures in a system for controlling an actuator (14) determining the position of a member for modifying the state of a gas-turbine engine, the system including a sing...  
WO/2014/052043A1
An example variable vane scheduling method includes adjusting variable vanes from a position based on a first schedule to a position based on a different, second schedule in response to a control feature. An example method of controlling...  
WO/2014/050163A1
This gas turbine cooling system (30) is equipped with: a cooler (31) that produces cooling air by cooling compressed air extracted from an air compressor (11); a cooling air compressor (34) that supplies the cooling air to a combustion t...  
WO/2014/046842A1
A nacelle assembly includes a thrust reverser moveable between a stowed position and a deployed position, a variable area fan nozzle, a motor to move the variable area fan nozzle, a drive shaft including a first portion coupled to the mo...  
WO/2014/046965A1
A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.  
WO/2014/043079A1
An assembly includes a synchronizing ring, a vane arm, and a multi-axis joint. The multi-axis joint connects the synchronizing ring to the vane arm and provides the vane arm with movement about a first pivot axis and a second pivot axis.  
WO/2013/038085A3
Method for monitoring the volumetric efficiency of a high-pressure pump of a turbomachine hydraulic regulation system comprising a high-pressure volumetric pump delivering a flow rate Q, dependent on an engine speed N of the turbomachine...  
WO/2014/039934A1
A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.  
WO/2014/007895A3
A variable vane assembly includes a damper positioned between a platform and a trunnion. The damper is comprised of a resilient material.  
WO/2014/031634A2
An on line optical inspection and monitoring system is externally mounted to existing man way service access within the combustor housing. A replacement man way cover having an optical window is mounted to the combustor housing. One or m...  
WO/2014/031199A2
A method of protecting operating margin of the gas turbine engine includes calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine that has a compressor section with variable vanes that are movable subject ...  
WO/2014/028270A1
A bumper assembly includes a bracket and a pad. The pad is connected to the bracket by a first rivet. Additionally, a synchronizing ring assembly for a gas turbine engine includes a ring section and a bumper assembly. The bumper assembly...  
WO/2014/023892A1
The invention relates to the field of turbine engine injection tubes and more specifically to a turbine engine injection tube (101) including: a first set of transfer tubes (102) connected so as to form a main circuit for supplying fuel ...  
WO/2014/020275A1
The invention relates to a constant-volume combustion chamber (10) for an aircraft turbine engine, including a compressed-gas intake valve (22) capable of adopting an open position, as well as a closed position in which said valve preven...  
WO/2014/022065A1
A stator assembly includes a case including an arcuate wall having an aperture with circumferentially spaced first lateral surfaces. A stator vane has an outer platform with a notch. An anti-rotation lug has a base that is received in th...  
WO/2014/022392A1
A gas turbine engine includes a jumper tube that extends through a first passage and a second passage.  
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/2014/022396A1
A baffle within a gas turbine engine includes a cylindrical flange with a multiple of holes at least partially therearound.  
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/2014/018727A1
A method and system for establishing sets of blade frequency values for each rotating blade of a rotor assembly at two or more different points in time and determining an indication of blade health from the change in the blade frequency ...  
WO/2014/014870A1
A temperature probe includes a flange, a support structure, thermocouple wires, and guide plates. The flange has a midline. The support structure is attached to the midline and extends away from the flange. The thermocouple wires extend ...  

Matches 501 - 550 out of 8,852