| Document |
Document Title |
|
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...
|
|
WO/2013/160626A1 |
An aircraft turbomachine comprising at least one body rotating at speed N1 and a monitoring system (1) comprising: - a regulation module (REG) comprising at least one regulation measurement path (A, B) suitable for obtaining a measuremen...
|
|
WO/2013/154640A2 |
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/2013/154646A1 |
A core flowpath through a low pressure compressor section of a gas turbine engine includes an outer diameter, which has a slope angle relative to an axis defined by the core flowpath. The slope angle is a slope angle that is operable to ...
|
|
WO/2013/154651A1 |
A method of managing a gas turbine engine variable area fan nozzle includes the steps of evaluating an icing condition to determine the likelihood of ice presence. A variable area fan nozzle position is altered if ice is likely present o...
|
|
WO/2013/151842A1 |
An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a d...
|
|
WO/2013/151841A1 |
A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engin...
|
|
WO/2013/149252A1 |
A turbine blade (22) for a gas turbine engine is disclosed. The turbine blade (22) can include at least one internal cooling path (64, 76), and an internal vane (100, 200) disposed in the at least one internal cooling path (64, 76). The ...
|
|
WO/2013/144524A1 |
The actuating device comprises: · a fixed portion forming a frame comprising an inlet intended to receive a fluid, a main outlet and a sampling outlet and return means for exerting a mechanical force on a movable portion; · a movable p...
|
|
WO/2013/144120A1 |
The invention relates to a method and to a device for safely operating a gas turbine plant (1), the operation of which is both controlled by at least one process controller (2) that at least triggers and/or influences operation-relevant ...
|
|
WO/2013/139797A1 |
The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve (9) and at least one burner (12) of a gas turbine (1) during the operation of the gas turbine (1). In order to de...
|
|
WO/2013/139904A1 |
The invention relates to a method for determining at least one firing temperature for controlling a gas turbine (20) that comprises at least one compressor (12), at least one combustion chamber (13) and at least one turbine (15), compres...
|
|
WO/2013/139974A1 |
The invention relates to an ignition unit (200) for a turbojet engine, said unit comprising: an electrical power supply (201), a single control channel (202) to receive a control signal from a computer, a main sparkplug ignition channel ...
|
|
WO/2013/138808A1 |
A gas turbine engine (100) configured to operate using a liquid fuel and a gaseous fuel may include a combustor system (20) fluidly coupled to a compressor system (10) and a turbine system (70). The gas turbine engine may also include a ...
|
|
WO/2013/134020A1 |
A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarg...
|
|
WO/2013/130575A1 |
A turbine nozzle insert (7) of a gas turbine engine is disclosed. The insert (7) may comprise an elongated hollow body portion (9), a flange portion (1 1) formed at a first end of the elongated body portion (9), and a contact portion (13...
|
|
WO/2013/127995A1 |
A system and computer-implemented method for monitoring and diagnosing anomalies in a wheel-space of a gas turbine is implemented using a computer device coupled to a user interface and a memory device and includes storing a plurality ru...
|
|
WO/2013/130506A1 |
This disclosure describes embodiments of a system and device (100) for measuring corrosive components suspended in air flowing to a turbo-machine (102). The device (100) comprises a fluid circuit (202) with a detection module (206) havin...
|
|
WO/2013/126278A1 |
Method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources. The method includes providing first and second fuel sources, sensing the operational paramete...
|
|
WO/2013/124568A1 |
Fuel injector for a turbomachine. The invention relates to a fuel injector for a turbomachine, comprising a body (2) comprising means for the intake of fuel under pressure, a stop valve provided to supply a primary fuel circuit (31, 20),...
|
|
WO/2013/126279A1 |
System and method for tuning the operation of a turbine and optimizing the mechanical life of a heat recovery steam generator. Provided therewith is a turbine controller, sensor means for sensing operational parameters, control means for...
|
|
WO/2013/124566A1 |
The invention relates to a fuel injector for a turbomachine, comprising a body comprising a primary fuel circuit and a secondary fuel circuit supplied by a metering valve (15). A leak channel (36, 37, 38) extends from an area (32) fluidl...
|
|
WO/2013/123121A1 |
A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section extending downstream from an inlet in the...
|
|
WO/2013/123008A1 |
A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an i...
|
|
WO/2013/123006A1 |
A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section that extends from an inlet in the first s...
|
|
WO/2013/117271A1 |
The invention relates to a method for avoiding pump surges in a compressor (2), wherein a plurality of parameters of the compressor (2) are monitored during operation and a desired value range for the plurality of parameters is predeterm...
|
|
WO/2013/118880A1 |
A disc shaft center adjusting mechanism in a gas turbine comprises the following: exhaust gas diffusers (13) provided between a bearing case (11) and an interior wall (10) connected to the downstream side of a turbine; a plurality of str...
|
|
WO/2013/116034A1 |
A method of managing a gas turbine engine operating line includes detecting an air speed and a fan speed. A data table is referenced that includes a desired variable area fan nozzle position based upon air speed and fan speed. The detect...
|
|
WO/2013/116125A2 |
A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight...
|
|
WO/2013/115994A2 |
A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the compressor. This is particularly useful ...
|
|
WO/2013/115921A1 |
A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled ...
|
|
WO/2013/105406A1 |
Provided are a fuel supply device and a gas turbine electricity generation plant with which responsiveness to variations in the gas turbine load can be improved, and which can be manufactured easily, thereby reducing the manufacturing co...
|
|
WO/2013/103109A1 |
This burner comprises a burner outer cylinder, a cylindrical burner inner cylinder provided inside the burner outer cylinder, a compressed air flow channel demarcated between the burner outer cylinder and the burner inner cylinder, and a...
|
|
WO/2013/102098A1 |
A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which...
|
