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Patent Searching and Data


Matches 551 - 600 out of 9,007

Document Document Title
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 ...  
WO/2013/172892A3
An exemplary debris detection method according to one example embodiment of the present disclosure includes, among other things, monitoring turbomachine performance, and initiating a debris warning when an actual rate of change in turbom...  
WO/2014/014596A1
A gearbox for a gas turbine engine includes a housing that includes first and second housing portions interconnected by an intermediate housing portion to provide a generally U-shaped structure. Each of the first and second housing porti...  
WO/2013/154640A3
A mid-turbine frame (MTF) for a gas turbine engine includes an inner manifold directing air to a turbine rotor of the gas turbine engine.  
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/2014/008128A1
An outer diameter (OD) hex nut secures a hollow cooling rod to an outer case of an engine. The OD hex nut includes a flange portion and a hollow tube portion. The flange portion includes a central aperture for receiving cooling airflow a...  
WO/2014/008005A1
An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine, and using the compressed air to cool a se...  
WO/2014/008007A1
An exemplary system for delivering a turbomachine fluid to a supplied area is a pump configured to draw fluid from both a first container and a second container when operating in both a positive g-force environment and a negative g-force...  
WO/2014/008053A1
A disclosed fuel injector provides mixing of fuel with airflow by surrounding a swirled fuel flow with first and second swirled airflows that ensures mixing prior to or upon entering the combustion chamber. Fuel tubes produce a central f...  
WO/2014/008269A1
An assembly includes a torque box and a first bell crank. The torque box has a housing with an interior cavity. The first bell crank is pivotally supported from the housing and extends through the interior cavity. The first bell crank ha...  
WO/2014/008051A1
A disclosed airfoil health monitoring system and method obtains a signal comprising a waveform indicative of an airfoil path with a sensor. Features of the waveform are determined and compared waveform characteristics indicative of a vib...  
WO/2014/008129A1
A cooling apparatus bifurcates and regulates cooling airflow provided to a mid-turbine frame. A flow metering tube includes a top portion and a tube portion, wherein the top portion includes a first central aperture that directs a first ...  
WO/2014/004069A1
A method of co-firing fuel within a gas turbine engine (5). The method may include injecting a first fuel (80) into a combustion system (20) of a gas turbine engine. The first fuel may include a high energy liquid fuel. The method may al...  
WO/2013/147944A3
A method of controlling a turbine engine (100). The method may include adjusting a position of a plurality of guide vanes (15) of a compressor (10). The adjusting the position of the plurality of guide vanes (15) may be a function of a c...  

Matches 551 - 600 out of 9,007