General Electric Company

S.p.m. Flow Control, Inc.

Qm Power, Inc.

Other

Bristol-myers Squibb Compnay

Spm Oil & Gas Inc.

Scott Hunter

Joel Francis Kirk

John Joseph Rahaim

Daniel Fusinato

Brandon Wayne Miller

Charles J Flynn

Cooper N Tracy

Thomas Ory Moniz

Bhaskar Nanda Mondal

Steven Alan Ross

Nadiya V Fuller

Caleb R Hunter

Ryan D Hunter

Arthur William Sibbach

Scott Alan Schimmels

Patrick Michael Marrinan

Curtis Walton Stover

Brian Christopher Witkowski

Michael Robert Melzak

Ching-Pang Lee

John E Macor

Jeffrey Douglas Rambo

Jeffrey Donald Clements

Saleem Ahmad

Douglas G Batt

Joseph Anthony Tino

Brian C Witkowski

Satheesh Kesavan Nair

Qingjie Liu

Kevin Samuel Klasing

Tarun Kumar Maishal

Ryan T Roehm

Jeff Myers

Andrew J Hank

Ben Ward

Geoffrey Whitener

Paul Pezzi

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.

Passive control of gas turbine clearances using ceramic matrix composites inserts

A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.

Gas turbine engine having a hydraulic fan brake

A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.

Turbine engine having a bleed system

Kits for a cover for a universal joint of a driveshaft include at least a first section and a second section of a cover, at least two cover fasteners, and at least one driveshaft fastener. The at least two cover fasteners configured to connect the first section to the second section, and the at least one driveshaft fastener configured to connect the cover to the driveshaft or to a yoke of the driveshaft without any portion of the cover contacting the universal joint. The kits also include a plurality of inserts and/or a plurality of pads configured to allow the cover to adapt to driveshafts of varying diameters without changing the size or shape of the cover itself.

Cover for a universal joint of a driveshaft

A cover for a universal joint of a driveshaft comprises a first section, a second section, at least two cover fasteners, and at least one driveshaft fastener. At least a first cover fastener of the at least two cover fasteners is configured to connect a first section first edge to a second section first edge. At least a second cover fastener of the at least two cover fasteners is configured to connect a first section second edge to a second section second edge. The at least one driveshaft fastener is configured to connect the cover to the driveshaft or a yoke thereof without any portion of the cover contacting the universal joint.

A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.

Bleed flow assembly for a gas turbine engine

A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

According to one aspect, data identifying a component is received, wherein the component is part of a system associated with a wellhead. A location at which the component is positioned relative to one or more other components is identified. The useful remaining operational life of the component is predicted based on at least an operational parameter specific to the location, and the operational history of the component or one or more components equivalent thereto. According to another aspect, a model representing at least a portion of a proposed system associated with a wellhead is generated, the model comprising a plurality of objects, each of which has a proposed location and represents an existing component. The useful remaining operational life for each object is predicted based on an operational parameter at the corresponding proposed location, and data associated with the respective operational history of the existing component.

Apparatus and methods for evaluating systems associated with wellheads

A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.

Modulated turbine cooling system

Disclosed are compounds of Formula (I): or a salt thereof, wherein Q, R, R, R, R, R, R, R, R, R, R, R, R, R, and Rare defined herein. Also disclosed are methods of using such compounds as inhibitors of Bruton's tyrosine kinase (Btk), and pharmaceutical compositions comprising such compounds. These compounds are useful in treating, preventing, or slowing the progression of diseases or disorders in a variety of therapeutic areas, such as autoimmune diseases and vascular disease.

Carbazole derivatives

A method for high speed switching comprises receiving voltage inputs at a bridge rectifier, receiving a logic input signal at an optical isolator and generating an output signal from the optical isolator based on the logic input signal, and driving a gate of a field effect transistor (FET) via the output signal of the optical isolator, wherein a source of the FET is connected to a negative output of the bridge rectifier and a drain of the FET is connected to a positive output of the bridge rectifier through a load. The method further includes limiting current flowing to the gate of the FET through first and second resistors and first and second diodes connecting the voltage inputs to the gate of the FET and limiting voltage to the gate of the FET below a maximum voltage rating of the FET by a Zener diode connected to the gate of the FET.

High speed switching solid state relay circuit

Growing community of inventors

Arlington, TX, United States of America

Scott Hunter