Goodrich Corporation

Rohr, Inc.

Other

Goodrich Corpration

Daniel Paul Christy

Claude Marc Hubert

Galdemir Cezar Botura

Michael John Layland

David B Sweet

Keith Towers Brown

Paul D Stoner

Derek Hass

Stanley G Prybyla

David Louis Brittingham

David Cenit Flosdorf

Daniel Lobo

Claude M Hubert

Paul Stoner

A method is disclosed, which can comprise via a transonic gas jet, depositing a thin film of LiPON on a substrate via a directed vapor deposition process. The transonic gas jet transports a thermally evaporated vapor cloud comprising the LiPON, wherein, the transonic gas jet comprises one of (a) substantially entirely nitrogen (N) gas; or (b) nitrogen (N) gas as a dopant in a concentration greater than 10% by volume in an inert carrier gas.

Methods for evaporating and depositing high vapor pressure materials

A method for protecting an aircraft component from ice formation uses a thermally conductive film. The film includes a polymer, an electrically conductive material, and a sufficient concentration of hexagonal boron nitride to provide adequate heat transfer properties, and have high thermal conductivity, peel strength, and shear strength. The films can include thermoset polymers, thermoplastic polymers, or blends thereof, and can also include reinforcing materials such as fiberglass, carbon fiber, metal mesh, and the like, and thermally conductive fillers, such as aluminum oxide, aluminum nitride, and the like. The films can be included in composite materials. The films can be used as part of a layered structure, and used in virtually any application, for example, various locations in aircraft, where heating is desirable, including nacelle skins, airplane wings, heated floor panels, and the like.

Methods of protecting an aircraft component from ice formation

An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer skin having at least one integrated heater element embedded in the composite material. An acoustic cellular core positioned between the outer and inner skin acts to attenuate fan noise from the engine. Covering the outer skin and overlying the acoustic core is a perforated erosion shield having a first set of openings that pass entirely thorough its thickness. The composite outer skin includes a second set of openings such that sound waves can pass from an inner barrel portion of the inlet lip through the erosion shield, outer skin, and heater element to the underlying acoustic cellular core.

Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein

An aircraft wing () comprising a structural casing () defining a leading edge, a fuel cell () within the structural casing (), a deicer () having electrical lines which receive a supply of electrical power from an onboard power source, and a trip line (). The trip line () is positioned to receive early contact upon impact of the wing by a bird or other foreign object and disruption of the trip line triggers termination of the supply of electrical power to the deicer ().

Aircraft wet wing

The invention includes a composite ice protection heater for an aircraft. The composite heater includes at least one electrically insulating layer, and at least one electric heater element comprising an electrically conductive layer bonded to the insulating layer. The conductive layer may include a pre-impregnated woven fabric that includes a plurality of threads that include an electrically conductive material, such as carbon or graphite fibers. The composite heater can be incorporated into a composite surface structure of an aircraft. The conductive layer and insulating layer may include a plurality of spaced openings through the layers that cooperate with an underlying open-cell matrix to attenuate noise at the associated surface of an aircraft. A desired electrical resistance of the conductive layer may be obtained by introducing a plurality of discontinuities in the layer, such as spaced holes or slits.

Composite ice protection heater and method of producing same

An electro-thermal ice protection system for an airfoil comprises: a metal foil heater including an integral parting strip, the metal foil heater configurable to cover at least a portion of a leading edge of the airfoil with the integral parting strip disposed along an air-stagnation zone of the leading edge; and a controller coupled electrically to the metal foil heater for controlling electrical energy from a power source to the metal foil of the heater in accordance with a pulse duty-cycle and for controlling power to the parting strip of the heater to maintain the air-stagnation zone virtually free of ice formation. A method of making an exemplary metal foil heater for use in ice protection of an airfoil comprises the steps of: preparing a sheet of Titanium foil in a rectangular shape having a length substantially greater than a width thereof for covering at least a portion of the leading edge of the airfoil; applying a layer of Nickel material over an area along each width edge of the Titanium foil; applying a layer of Copper material over the Nickel layer along each width edge of the Titanium foil; and attaching conductor wires to the Copper layers at each width edge.

Low power, pulsed, electro-thermal ice protection system

Growing community of inventors

Akron, OH, United States of America

Daniel Paul Christy