Rohr, Inc.

Rtx Corporation

Steven M Kestler

Joseph V Mantese

Vijay V Pujar

Jay Francisco

Sarah Lohman

Gurkan Gok

Manuel Muñoz

Mark R Gurvich

Georgios S Zafiris

Wenping Zhao

Jose S Alonso-Miralles

Xiaolan Hu

Jennifer Davis

Stuart James Byrne

Keith Towers Brown

Bryce Tyler Kelford

John J Gangloff, Jr

Jeffrey A Anderson

George Hoehn

Yuan Li

Sameh Dardona

Jeffrey Harasha

Prithvi Sundar

Kevin W Teets

Callum Bailey

Isabel Cole

Pamela Monttserrat Lopez Simental

Maxwell Robertson

Manuel Munoz

Kevin Teets

Jr John J Gangloff

Keith T Brown

Stuart J Byrne

A method for dehumidifying a perforated acoustic skin includes disposing a sheet of material over a perforated acoustic skin, sealing a periphery of the sheet of material to the perforated acoustic skin to form a cavity between the sheet of material and the perforated acoustic skin, disposing at least one dehumidifier in fluid communication with the cavity, and activating the dehumidifier to remove moist air from a core of the perforated acoustic skin. The dehumidifier(s) may be mounted to the sheet of material.

Dehumidifier quilt systems and methods

A formation method is provided during which a cellular core is provided. The cellular core includes a plurality of cavities that include a first cavity. Each of the cavities extends through the cellular core. A metal substrate is disposed within the first cavity. The metal substrate is electroplated to form a septum within the first cavity. The septum is bonded to the cellular core.

Forming acoustic panel with multi-layered septum(s)

An aircraft ice protection system includes a frequency a frequency dependent susceptor coupled to a critical surface of an aircraft. A radio frequency (RF) energy source is configured to apply RF energy to the frequency dependent susceptor. The aircraft ice protection system is configured to selectively operate in a susceptor absorbing mode and a water absorbing mode. The aircraft ice protection system operates in the susceptor absorbing mode until a Faraday layer associated with ice formed on the critical surface reaches a target characteristic. When the target characteristic is met, the aircraft ice protection system initiates the water absorbing mode.

Ice protection system including frequency dependent susceptor

An assembly is provided for a structure. This assembly includes a composite skin and a thermal anti-icing system. The composite skin extends between an exterior surface and an interior surface. The thermal anti-icing system includes a susceptor and a waveguide. The susceptor and the waveguide are integrated into the composite skin between the exterior surface and the interior surface. The waveguide is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

Integrated microwave thermal anti-icing system

An assembly is provided for an aircraft structure. This aircraft structure assembly includes an acoustic panel and a thermal anti-icing system. The acoustic panel includes an exterior surface. The thermal anti-icing system includes a susceptor and a microwave system. The susceptor is configured with the acoustic panel. The microwave system is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

Microwave thermal anti-icing system for aircraft acoustic structure

An acoustic panel system is provided that includes a perforated first skin, a second skin and a core. The core is connected to the perforated first skin and the second skin. The core includes a plurality of chambers and a first constriction. Each of the chambers extends vertically through the core between the perforated first skin and the second skin. The chambers include a first chamber. The first constriction is configured to divide the first chamber into a plurality of fluidly coupled sub-chambers. The first constriction is configured from or otherwise includes a shape memory material.

Acoustic panel with reconfigurable chamber constrictions

A sensor array system includes a skin. The sensor array system includes a lattice network coupled to a portion of the skin. The lattice network includes a plurality of interconnects and a plurality of nodes. The plurality of nodes are respectively defined by an intersection of two or more interconnects of the plurality of interconnects. The sensor array system includes a first sensor electrically connected to the lattice network at a first node of the plurality of nodes.

Flexible sensor system for prognostic health monitoring of composite aerostructures

A method for gathering flight load data for a gas turbine engine includes providing a plurality of blocker doors rotatably mounted to a translating sleeve and a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit; and connecting the data acquisition unit to at least one sensor in communication with the translating sleeve.

System and method for gathering flight load data

An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

Method and apparatus for aircraft anti-icing

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes an aircraft propulsion system and a microwave system. The aircraft propulsion system structure includes an exterior surface, an internal cavity and a susceptor thermally coupled to the exterior skin and within the internal cavity. The microwave system is configured to direct microwaves to the susceptor for melting and/or preventing ice accumulation on the exterior surface.

Thermal-anti-icing system with microwave system

An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.

A panel includes a corrugated base with base corrugations configured from first base segments and second base segments. A first of the base corrugations includes a first of the first base segments and a first of the second base segments that is non-parallel to the first of the first base segments. The first of the base corrugations forms a first channel that extends laterally between and longitudinally along the first of the first base segments and the first of the second base segments. A corrugated stringer includes a plurality of stringer corrugations arranged longitudinally along and within the first channel. The stringer corrugations are configured from first stringer segments and second stringer segments. A first of the stringer corrugations includes a first of the first stringer segments and a first of the second stringer segments that is non-parallel to the first of the first stringer segments.

Structured panel with non-parallel cavity walls

A manufacturing method is provided. During this method, a panel is provided that includes non-conductive material and a plurality of conductive elements at least partially embedded within the non-conductive material. The conductive elements include a first conductive element. An electric current is applied to the first conductive element such that the first conductive element produces a signature. A location of the first conductive element in the panel is determined based on the signature. An aperture is formed in the panel based on the determined location of the first conductive element.

Locating an aperture based on a signature of an embedded conductive element

A translating wire harness includes a first portion, a second portion configured to translate relative to the first portion, a wire spool coupled to the first portion, and an electrical wire at least partially wound onto the wire spool, wherein the electrical wire at least partially unwinds from the wire spool in response to the second portion translating away from the first portion, and the electrical wire at least partially winds into the wire spool in response to the second portion translating towards the first portion, a portion of the electrical wire extending between the first portion and the second portion remains taught during translating of the second portion both (a) away from and (b) towards the first portion.

Growing community of inventors

San Diego, CA, United States of America

Steven M Kestler