Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 551 - 600 out of 8,852

Document Document Title
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...  
WO/2014/003985A1
An exemplary valve device for controlling flow of a turbomachine fluid includes a housing having a first inlet at a first elevation, a second inlet at a second elevation higher than the first elevation, and an outlet. A flow control memb...  
WO/2014/004494A1
A method for model-based control of a gas turbine engine is disclosed. An operating point of the gas turbine engine is generated from measured parameters using a component-level model. The component-level model is analytically linearized...  
WO/2014/004001A1
A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of ...  
WO/2014/002272A1
With the present invention, during a light load wherein the effective power of a generator (110) as detected using a current sensor (5501) and a voltage sensor (5502) is equal to or less than a prescribed value P1, a controller (600) out...  
WO/2013/153052A3
A self-rectifying turbine system has a turbine (10) with impulse turbine blades (3). There is a set of first guide vanes (5) on one axial side of the rotor, and second guide vanes (6) on the other axial side of the turbine (10). A contro...  
WO/2014/001230A1
The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially comprises at least one compressor, a first combustor which i...  
WO/2014/004984A1
An LNG fuel system for gas turbine engine systems is disclosed that allows more efficient management of cryogenic fuels such as LNG to reduce emissions and improve engine efficiency. In one configuration, an intercooled, recuperated gas ...  
WO/2014/003716A2
A method of setting actuator position of a variable geometry turbine linked to drive a compressor for a compression ignition engine using exhaust gas recirculation. The method includes detecting an engine transient event; determining cur...  
WO/2013/191889A1
An example method of controlling a flow enhancement device includes providing a flow enhancement device that is configured stabilize a flow of air near a nacelle. The flow enhancement device has a first setting and a second setting that ...  
WO/2013/192523A1
A gas fuel turbine engine (100) may include a gaseous pilot fuel supply, a first main fuel supply, and a second main fuel supply. The first main fuel supply may provide gaseous fuel to a first plurality of fuel injectors (30), and the se...  
WO/2013/190237A1
The invention relates to a method and device for adjusting a threshold value of a fuel flow rate, which includes: a step of obtaining (E20) a first estimate (E1) of a fuel flow rate injected into a combustion chamber of a turbine engine ...  
WO/2013/191941A1
The present invention relates to an exhaust-gas turbocharger (1) having a turbine (2) which is provided with an adjustable turbine geometry and/or with a wastegate; and having an actuator (11) which is connected by means of a coupling ro...  
WO/2013/190218A1
The method of adjusting a reference value of at least one parameter that influences the thrust of a gas turbine engine powering an aircraft during a phase of flight of this aircraft comprises: — a step (E20) of obtaining a current valu...  
WO/2013/191877A1
An airfoil includes an airfoil body that extends between a leading edge and a trailing edge, a suction side and a pressure side, and a first end and a second end. At least one fitting is located on at least one of the first end and the s...  
WO/2013/192378A1
A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis ...  
WO/2013/192525A1
A gas turbine engine (100) may include a plurality of pilot fuel supply lines (148) configured to supply liquid fuel. Each pilot fuel supply line may be coupled to a respective fuel injector (30). The turbine engine may include a plurali...  
WO/2013/188074A1
An exemplary flow control device assembly for a turbomachine includes a flow control device configured to move between a first position and a second position. The flow control device in the first position forces more flow through a plura...  
WO/2013/184336A1
An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The f...  
WO/2013/184608A1
A method (1200) for collecting and processing vibration data from a turbine engine system (148) is disclosed. The method comprises: receiving (1202) engine data from the turbine engine while in service, where the engine data include vibr...  
WO/2013/184430A1
A rotor assembly for a gas turbine engine includes a rotor configured for rotation about an engine axis, the rotor including an aft surface including a rotor slot and a cover plate attached to the aft surface of the rotor, the cover plat...  
WO/2013/184264A1
An integrated fuel pump and control system includes a pump assembly with an inlet and an outlet; a motor connected to the pump assembly to provide power to the pump assembly; a controller to regulate the speed of the motor; and a housing...  
WO/2013/184329A1
A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream ...  
WO/2013/181399A1
An assembly includes a first part, a second part, a sleeve, and a fastener. The first part has a first hole with a threaded portion therein. Additionally, the first hole has a first counterbore. The second part has a second hole with a s...  
WO/2013/181312A1
A damper (36) for a turbine rotor assembly (24) of a gas turbine engine is disclosed. The damper includes a width dimension (12), a height dimension (14), and a length dimension (10), and a forward plate (76) and an aft plate (78). The a...  
WO/2013/180917A1
A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compress...  
WO/2013/181254A1
An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mecha...  
WO/2013/180939A1
A lubrication system includes a bearing compartment. A main reservoir is fluidly connected to the bearing compartment by a main supply passage. A main pump is arranged in the main supply passage configured to provide fluid from the main ...  
WO/2013/181231A1
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 and positioned radially outward from the ID shroud. A plur...  
WO/2013/181311A1
A damper (36) for a turbine rotor assembly (24) of a gas turbine engine is disclosed. The damper includes a width dimension (12), a height dimension (14), and a length dimension (10), and a forward plate (76). The damper further includes...  
WO/2013/176863A1
An airfoil includes an airfoil body having an internal cavity. A thermostatic valve is located at least partially within the internal cavity. The thermostatic valve is configured to passively control fluid flow into the internal cavity i...  
WO/2013/176919A1
A debris discourager for a gas turbine engine is rotatable about an engine axis and extends between a fore end and an aft end. A portion of the debris discourager includes a non-uniform surface that generates a wind flow to prevent debri...  
WO/2013/177030A1
A method and device for modifying a gas turbine engine (100) is disclosed herein. The method for modifying a gas turbine engine (100) includes accessing a first outward end (717) of a first tube (713, 715) installed in the gas turbine en...  
WO/2013/172892A2
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/2013/167836A1
Method for assembling an actuator (62) for air bleed valves (48) arranged between low-pressure and high-pressure compressors of a turbine engine, the actuator including a piston rod (68) surrounded by a spacer (64) that extends the pisto...  
WO/2013/165771A1
A disclosed gas turbine engine includes a core engine defined about an engine centerline axis, the core engine including a compressor section driven through a shaft by a turbine section. A core nacelle surrounds the core engine and a fan...  
WO/2013/162886A1
Rotary vane actuator operated air valves associated with gas turbine engines are disclosed. An example gas turbine engine may include a fan, a compressor, a combustor, and a turbine in a serial flow relationship; a supply pipe arranged t...  
WO/2013/163604A1
A fuel injector (30) includes a flow path for fuel air mixture to a combustor (50) extending longitudinally through the fuel injector. The fuel injector may also include a liquid fuel gallery (56) at least partially encircling the flow p...  

Matches 551 - 600 out of 8,852