United Technologies Corporation

Raytheon Technologies Corporation

Other

Steven D Roberts

David C Pimenta

Paul R Senofonte

Richard W Monahan

Jocelyn Charis Damgaard

Matthew E Bintz

Timothy Dale

William S Pratt

Joseph J Czapski, Jr

Chung-Han Liou

Lisa I Brilliant

Martin Richard Amari

Yuan Dong

Adam Lee Hart

George Alan Salisbury

Andrew J Murphy

Isaac Jon Hogate

Weston Behling

Taryn Narrow

Jason Leroux

Jordan T Wall

Robert B Fuller

Daniel J Monahan

Ryan M Stanley

Lucas D Sorensen

Kenneth F Tosi

Diane C Kjelby

Adam Hart

Jocelyn C Damgaard

Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

Inserts for slotted integrally bladed rotor

A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

Continuous wedge vane arm with failsafe retention clip

A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.

Nested direct vane angle measurement shaft

A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

Rotor blade for a gas turbine engine

Tracks (), fastened to static structure of an aircraft engine nozzle, guide sliders () journaled in struts () fastened to a flap () of the nozzle. Each slider and attached journal axle or bolt () is formed of cobalt, and each track slider surface () and journal bushings () are formed of a nickel alloy to reduce wear from rubbing. Track slides () are mounted to the static structure of the nozzle by blind bolts () having a tool recess () at its threaded tip to prevent the bolt () from turning as a nut is secured. Each slider has limited rotation due to a pin (), thereon engaging a slot in a tab () of the bushing () to assist in inserting the slider () into the beveled ends of the tracks (), when mounting or replacing a flap.

Sliding nozzle flap assembly

An assembly for a turbine engine includes an inner platform, and outer platform and a plurality of structural inlet guide vanes. The outer platform circumscribes the inner platform. The structural inlet guide vanes are arranged around an axis, and extend radially between and are connected to the inner platform and the outer platform. A first of the structural inlet guide vanes includes a structural vane body that is configured from or otherwise includes an organic matrix composite.

Organic matrix composite structural inlet guide vane for a turbine engine

A multi axis slide carriage system includes a channeled track, a slide, a shaft and a slide carriage bracket. The channeled track extends along a first axis. The slider slides along the first axis within the channeled track, and includes a slider segment aperture extending therein along a second axis. The shaft includes a slider segment connected to a carriage bracket segment. The slider segment slides along the second axis within the slider segment aperture. The slide carriage bracket is positioned adjacent to the channeled track, and is connected to the carriage bracket segment.

Multi axis slide carriage system

A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket.

Flexible seal system for a gas turbine engine

A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.

Flexible seal for gas turbine engine system

A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections.

A hanger system includes a pin with a head section which defines a pin axis. A clip assembly captures the head section to permit movement of the pin within a hanger in a direction transverse to the pin axis. A fastener which retains the clip assembly to the hanger.

Retainer for suspended thermal protection elements in a gas turbine engine

A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline.

A harness for an ABS therapeutic ball allows a user to perform aerobic exercises while seated on the ABS therapeutic ball. The harness includes a stabilizer portion having circumferential straps extending therefrom. A handle is positioned between the circumferential straps proximate a joining area thereof. An adjustment strap having a self fastening system also extends from the stabilizer portion of the harness and interacts with the joining area of the circumferential straps to provide a single, overall size adjustment of the harness to accommodate various sizes of ABS therapeutic balls. Once installed onto an ABS therapeutic ball, the user may perform various aerobic exercises while seated on the ABS therapeutic ball and firmly grasping the handle of the harness. The harness thus provides a secure, no-slip, and stable platform for aerobically exercising on the ABS therapeutic ball.

Growing community of inventors

Moodus, CT, United States of America

Steven D Roberts