United Technologies Corporation

Raytheon Technologies Corporation

Intuit, Inc.

Solar Turbines Inc.

Christopher Marc Dye

Gabriel L Suciu

Brian D Merry

Steven B Johnson

Ioannis Alvanos

Frederick M Schwarz

Nathan A Snape

Joseph Brent Staubach

Jorn Axel Glahn

Hung Duong

Carol Ann Howe

Nankun Huang

Allan R Penda

Robert E Bamford

Stephen P Muron

Keshava Basavapatna Kumar

Nagendra Somanath

Karl L Hasel

Michael E McCune

James W Norris

Glenn Levasseur

James S Elder

Arthur M Salve, Jr

Wesley K Lord

William Arthur Sowa

Jon A Marx

David W J Franklin

William K Ackermann

Harold W Hipsky

Craig A Nordeen

Om Parkash Sharma

Douglas Michael Berczik

Steven J Bauer

Jason Elliott

Matthew J Howlett

Michael F Cass

Richard E McVickar

Azhar M Zuberi

Angelo Vincent Marasco

Jay Bhatt

Hasel Karl

Matthew G Dixon

Alvanos Ioannis

Brian D Marry

A gas turbine engine includes, among other things, a propulsor section including a rotor, a gear train, a low spool and a high spool. A static structure includes a first case and a second case. A mount system includes a forward mount and an aft mount arranged in a plane containing an engine axis of rotation. The forward mount is secured to the first case. The aft mount is secured to the second case.

Engine mount system for a gas turbine engine

A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.

Gas turbine engine front architecture

A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

Gas turbine engine with low stage count low pressure turbine and engine mounting arrangement

A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section is greater than about 7.

Gas turbine engine compressor arrangement

A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.

Gas turbine engine oil tank

A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.

Spoked rotor for a gas turbine engine

During an image-analysis technique, the system calculates features by performing image analysis (such as optical character recognition) on a received image of a document. Using these features, as well as spatial and grammatical constraints, the system determines a layout of the document. For example, the layout may be determined using constraint-based optimization based on the spatial and the grammatical constraints. Note that the layout specifies locations of content in the document, and may be used to subsequently extract the content from the image and/or to allow a user to provide feedback on the extracted content by presenting the extracted content to the user in a context (i.e., the determined layout) that is familiar to the user.

Layout reconstruction using spatial and grammatical constraints

A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

Gas turbine engine with low stage count low pressure turbine

A computing device acquires a video of a tax document utilizing a video camera such as a webcam. The video is analyzed to detect a first motion of the tax document, such as sufficient shaking or movement of the tax document, satisfying first pre-determined criteria that results in the computing device being prompted or requested by the user to take an image of the tax document. After the first pre-determined criteria has been satisfied, the user is instructed to hold the tax document steady. Subsequent video frames are analyzed to detect a second motion or the tax document being sufficiently still or steady, in response to which an image of the tax document is acquired and processed to extract data of the tax document from the acquired image and populate corresponding fields of the electronic tax return.

Methods systems and computer program products for motion initiated document capture

An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis and includes first and second sides. A first geartrain includes one or more shafts rotatable about axes perpendicular to the first side of the accessory gearbox and a second geartrain includes one or more shafts rotatable about axes perpendicular to the second side of the accessory gearbox. A driven gear set defines an input axis and drives first geartrain and the second geartrain about corresponding first and second drive axes parallel to the input axis.

Accessory gearbox with tower shaft removal capability

A turbine engine is disclosed that includes a fan case surrounding a fan. A core is supported relative to the fan case by support structure, such as flow exit guide vanes, which are arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage. In one example, the example turbine engine includes a gear train arranged between the fan and a spool. The gear train is axially aligned and supported by the inlet case. An intermediate case is arranged axially adjacent to the compressor case. The support structure is arranged axially forward of the intermediate case. In one example, the support structure is axially aligned with the compressor case.

Methods, systems and articles of manufacture for location-based speech recognition for preparation of an electronic tax return.

Location-based speech recognition for preparation of electronic tax return

Growing community of inventors

San Diego, CA, United States of America

Christopher Marc Dye