General Electric Company

Unison Industries, Inc.

Ronald Bruce Schofield

George Elliott Moore

James Fitzgerald Bonar

Jeffrey Lee Mason

Benjamin James Schumacher

Seth Michael Ray

Michael Ralph Storage

Sudeep Pradhan Sadananda Rao

Naleen Kumar Verma

Daniel Drew Smith

Dennis Alan McQueen

Dharmaraj Pachaiappan

Thomas Charles McCarthy

Stephen G Matava

Robert David Perry

Ted Lewis Robertson

Joseph John Bischof

Walter Arthur Hundley, Jr

Eileen Mary Corcoran

Scott Richard Lawrence

Ronald Eugene Bruskotter

Kinga Lucja Rybinska

Stefka Petkova Petkova

A gas turbine engine including a wall assembly, a seal assembly, and a member extended through the wall assembly is provided. The wall assembly defines an opening through which the member is extended, and the wall assembly defines a first side and a second side opposite of the first side along a direction of extension of the member through the wall assembly. The seal assembly includes a retaining portion extended at least partially co-directional to the member. The retaining portion is configured to couple around the member and extend through the opening. The seal assembly further includes a locking portion configured to sealingly attach to the wall assembly and the retaining portion at an interface between the locking portion and the retaining portion.

Seal assembly

A ventilation system includes a cavity, a fluid motive force device, and a motive fluid supply system. The cavity includes different ventilation level requirements for a plurality of modes of operation. The fluid motive force device includes a suction port, an outlet port, and a motive fluid inlet port. The suction port is coupled in flow communication with the cavity to be vented. A flow supply to the motive fluid inlet port determines a ventilation flow through the suction port. The motive fluid supply system is coupled in flow communication with the motive fluid inlet port. An operation of the motive fluid supply system determines a flow of motive fluid from the motive fluid supply system to the motive fluid inlet port. The flow of motive fluid to the motive fluid inlet port generates a ventilation flow through the suction port approximately matching a current ventilation demand of said cavity.

System and method for engine eductor powered by alternate managed air system

A threaded element for a mechanical joint includes a body including threads and a visual torque indicator disposed on the body, the torque indicator including a strain-responsive material configured to change visual appearance in response to the application of a strain of a predetermined first magnitude thereto.

Visual torque indication for threaded joints

A method and assembly for conveying heat from a heat exchanger having a housing defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the housing have a first side and a second side, opposite the first side where the housing includes at least one aperture extending through the housing from the first side to the second side and where the aperture is fluidly separate from the fluid pathway and heat from liquid flowing through the fluid pathway is transferred via at least one of conduction or convection to the housing.

Thermal management system

A shroud configured for installation on a component of a machine includes a shroud body including a plurality of arcuate sections hingedly coupled together, and a closure assembly including an engagement member and a receiving member. The plurality of arcuate sections include a first arcuate section hingedly coupled to one of the arcuate sections at a first edge and including the engagement member at an opposing second edge, and a second arcuate section hingedly coupled to one of the arcuate sections at a first edge and including the receiving member at an opposing second edge. The shroud body is configured to transition between an open configuration in which the engagement member and the receiving member are spaced apart from one another and a closed configuration in which the engagement member engages with the receiving member, the closure assembly maintaining the shroud body in the closed configuration.

Cooling shrouds

A pressure sensing device with a tubular pressure port including an internal chamfer adjacent to a deflectable diaphragm, and/or a hydrophobic or superhydrophobic coating applied to at least a portion of the tubular pressure port, the internal chamfer, and/or the deflectable diaphragm. The internal chamfer and/or the hydrophobic or superhydrophobic coating are configured at least in part to reduce adhesive forces between condensation and the surface of the tubular pressure port, to reduce the tendency for capillary action to draw condensation towards the deflectable diaphragm, and/or to increase the tendency for capillary action or gravity to draw condensation away from the deflectable diaphragm and out of the tubular pressure port.

Pressure sensing devices, systems, and methods for alleviating interference from moisture

A method and system for an air management system (AMS) is provided. The AMS includes a jet pump assembly including a motive air inlet, a plurality of suction inlets, and a single outlet. The AMS also includes a supply piping arrangement including a conduit configured to channel relatively higher pressure air from a compressor to the motive air inlet, a conduit configured to channel relatively higher pressure air from the compressor to at least one of the plurality of suction inlets through a shutoff valve, and a conduit configured to channel relatively lower pressure air from the compressor to at least one of the plurality of suction inlets. The AMS further includes an outlet piping arrangement configured to channel outlet air from said jet pump assembly to a distribution system. A pressure regulation strategy of the motive jet pump flow allows optimization of engine fuel burn and/or thrust, depending on which is most important to the aircraft during any flight phase.

Method and system for air management of aircraft systems

A method and system for a jet pump is provided. The jet pump system includes a pre-mixing bowl includes a nozzle, a mixing section at least partially surrounding the nozzle, and a first inlet opening configured to receive a first flow of fluid and direct the first flow of fluid to an inlet of the nozzle. The pre-mixing bowl further includes a second inlet opening configured to receive a second flow of fluid and to direct the second flow of fluid to the mixing section. The second inlet opening includes a first inlet opening area. The second inlet opening includes an entry angle into the pre-mixing bowl that is oblique with respect to the central axis. The pre-mixing bowl further includes a third inlet opening configured to receive a third flow of fluid to direct the third flow of fluid to the mixing section.

Method and system for a short length jet pump with improved mixing

A check valve includes a valve housing and at least one control member. The valve housing includes a sidewall and an opening extending therethrough. The sidewall defines the opening and includes at least one recess formed therein. Each control member is rotatably coupled to the valve housing within the sidewall recess, and each control member is configured to allow flow of fluid through the valve opening in a first direction. Each control member is further configured to substantially prevent flow of fluid through the valve opening in a second direction that is opposite the first direction.

Growing community of inventors

Clarksville, OH, United States of America

Ronald Bruce Schofield