United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Michael Joseph Murphy

Sean P Zamora

Jeffrey R Lavin

Jorge I Farah

Robert E Malecki

Steven H Zysman

Curtis C Cowan

Stephen A Paul

Joshua V Wood

Frederick M Schwarz

Gary D Roberge

Kevin W Schlichting

Joel H Wagner

Bruce L Morin

Nigel David Sawyers-Abbott

Paul W Duesler

Brian Kenneth Holland

Meggan Harris

Shawn M McMahon

Dale William Petty

Andrew D Burdick

Gary J Dillard

Michael R Thomas

Oleg Petrenko

James P Allore

Justin R Urban

John R Buey

William W Rice

Timothy A Swanson

Andrew A Consiglio

Debora F Kehret

Brandon T Slaney

Henry Huizinga

Luis Coreano

Charles Waldo Haldeman, Iv

Stanley Keysa

Richard Scott

David W Lamarre

Glenn R Estes

Charles Waldo Halderman Iv

Shawn M Mcmahon

A face skin for an acoustic panel may comprise a sheet defining a first surface and a second surface. A plurality of slots may be formed through the face skin using abrasive blasting. Each slot of the plurality of slots may comprise a first semi-circular wall and a second semi-circular wall opposite the first semi-circular wall.

Composite skins having variable hole sizes and shapes formed using photomachining

An environmental sampling system includes a passage in an aircraft component and a removable collector disposed in the passage. The passage has an inlet at a first region and an outlet at a second region. When the aircraft component is in operation the first region is at a greater pressure than the second region such that air flows through the passage from the inlet to the outlet. The removable collector is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration to predict maintenance activity.

Environmental sampling system and method

Isolation seals for gas turbine engines are described. The isolation seals include an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end and a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body.

Isolation seals for gas turbine engines

A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle.

Gas turbine engine with short inlet, acoustic treatment and anti-icing features

A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed.

High performance convergent divergent nozzle

A variable nozzle apparatus may include a radially inward structure and a radially outward structure circumscribing the radially inward structure. An annular flow channel is defined between the radially inward structure and the radially outward structure. One of the radially inward structure and the radially outward structure includes a static portion and a moveable portion. The moveable portion may be to the static portion via helical threads and may thus configured to rotate circumferentially and translate axially relative to the static portion. Movement of the moveable portion relative to the static portion may change a radial dimension of the annular flow channel.

Variable nozzle apparatus

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

Nacelle deflection measurement assembly

A turbine engine cooling arrangement according to an example of the present disclosure includes, among other things, a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, a second airflow source including a second passage adjacent the first passage for conveying a second airflow, and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow. The first airflow and the second airflow stream over the heat exchanger in a parallel radial direction and a parallel axial direction. An engine inlet divides inlet air into the core flow, the first airflow, and the second airflow. A method of providing cooling air is also disclosed.

Heat exchanger arrangement for turbine engine

A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle in communication with a fan bypass flow path. An actuator assembly is operable to move a second fan nacelle section relative to a first fan nacelle section to vary a fan nozzle exit area and adjust fan bypass airflow, the actuator assembly extends at least partially into the fan bypass flow path.

Variable area fan nozzle

A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section.

Non-circular aft nacelle cowling geometry

A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an Environmental Control System (ECS) pre-cooler or an Air Oil Cooler (AOC) 'peaker' through a common inlet.

Thermal management system for gas turbine engine

An exhaust liner assembly including an interface between moveable parts includes a seal liner having a plurality of slots. The size of each slot varies with the circumferential position of the liner assembly to provide a stable cavity pressure within the interface to create a stable barrier about the entire circumference of the exhaust liner assembly.

Seal land with air injection for cavity purging

A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, and a second airflow source including a second passage adjacent the first passage for conveying a second airflow. A heat exchanger is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow.

A gas turbine engine includes a fan nacelle and a core nacelle spaced radially inwardly of the fan nacelle to define a bypass flowpath. The engine includes a scoop to direct air from the bypass flowpath into an engine core. The scoop is comprised of a first piece extending outwardly of an outer surface the core nacelle to define an air inlet and a second piece extending inwardly of the core nacelle to define an air outlet.

Retrofitable auxiliary inlet scoop

Growing community of inventors

Windsor, CT, United States of America

Michael Joseph Murphy