General Electric Company

United Technologies Corporation

Other

Raytheon Technologies Corporation

Rtx Corporation

Robert Russell Mayer

Mahmut Faruk Aksit

Bharat S Bagepalli

Donald William Peters

Nicholas W Kantany

Paul W Palmer

Edward Boucher

Kristine Marie Carnavos

Osman Saim Dinc

Konrad Roman Weeber

Christian Lee Vandervort

Wei Tong

Jonathan Lemoine

Charles D Stoner

Tracy A Propheter-Hinckley

Jorge I Farah

Glenn Levasseur

George J Kramer

Chris Vargas

Anthony P Cherolis

Christopher Treat

Andrew D Burdick

John H Mosley

Peter F Gero

James R Mayer

Peter Balawajder

David C Pimenta

Fernando K Grant

Andrew S Miller

Eric Baker

Eric Conrad Engsberg

Shu Liu

Stephanie Ernst

Igor S Garcia

A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

Synchronized air modulating system

An assembly is provided for a variable vane arrangement of a turbine engine. A platform extends circumferentially about a centerline and radially relative to the centerline between a first platform side and a second platform side. The platform includes a plurality of variable vane receptacles arranged in an annular array about the axial centerline, which variable vane receptacles include a first variable vane receptacle. The first variable vane receptacle is configured with a recess, a bore and a shelf. The recess extends longitudinally along a variable vane pivot axis into the platform from the first platform side to the shelf. The bore extends longitudinally along the variable vane pivot axis into the platform from the shelf. An insert includes a sleeve and a plate. The sleeve lines at least a portion of the bore. The plate is located within the recess adjacent the shelf.

Variable vane arrangement with vane receptacle insert(s)

Evidence-based computer knowledge acquisition, expression verification, and problem solving methods and systems are disclosed. Embodiments are described that include methods for automatically evaluating natural language expressions by processing an argument of an analysis of a natural language expression. Also included is the processing of one or more items of evidence associated with the argument, and determining a quality score for the argument and the one or more items of evidence. The arguments may be based on one or more criterion associated with the natural language expression.

Comparative expression processing

A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.

Gas turbine engine blade containment system

A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.

Gas turbine engine mid turbine frame bearing support

A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.

Cooling passages for a mid-turbine frame

The disclosure provides a system and methods of use pertaining to long-range fishing applications. One embodiment provides a long-range fishing-device delivery system that relies on a mounting shaft, a buoyancy module, and a fishing or payload module to house a variety of fishing devices such as a baited hook, an artificial lure, or a fishing accessory such as a depth sensor, temperature sensor, or fish finder. The delivery system leverages a launch force from an external launching apparatus such as a bow or slingshot to deploy the system and enclosed fishing device to a desired long-range location and depth within a body of water. Other embodiments are also disclosed.

Long-distance delivery system for fishing devices

A gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoins the first leg to a second leg, which is conical in shape. A seal is supported by the second leg.

Gas turbine engine seal carrier

A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.

An extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall and the impingement sheet. The baffle has a collector plenum area that receives impingement cooling air from the air supply plenum and a channel in fluid communication with the collector plenum and extending outside the air supply plenum with openings to allow impingement cooling air to pass therethrough and having a series of lands extending into the channel wherein the lands are located in proximity to impingement cooling air outlets in the inner wall.

Extended impingement cooling device and method

A combination for connecting a hot sheet and a cold sheet of a nozzle liner in spaced relationship apart includes a stud having a main body wherein the stud is attached to the hot sheet and a portion of the stud extends through an opening in the cold sheet. A support spaces the hot sheet and the cold sheet apart. A generally planar fastening collar is affixed to the portion of the stud extending through the cold sheet. A first length is defined by the portion of the stud extending through the cold sheet to a distal end of the stud. A second length is defined between a first planar surface of the collar facing the cold sheet and a second planar surface of the collar opposite the first surface. Each of the first and second lengths is less is less than a diameter of the main body of the stud.

Compact fastening collar and stud for connecting walls of a nozzle liner and method associated therewith

Growing community of inventors

Manchester, CT, United States of America

Robert Russell Mayer