Goodrich Corporation

Hamilton Sundstrand Corporation

B/e Aerospace, Inc.

Rohr, Inc.

Rosemount Aerospace Limited

Other

Collins Engine Nozzles, Inc.

Goodrich Corpration

Steven A Poteet

Blair A Smith

Vijay V Pujar

Katherine Urena Pimentel

Thomas Martz

Irene Rexwinkle

Gavin Charles Richards

David C McConnell

Marc E Gage

Zachary Cohen

Bradford D'Alessio

James Thompson Beals

Georgios S Zafiris

Xia Tang

John E Holowczak

Anthony M Mazany

Kevin M Rankin

Lance R Bartosz

Claude J Moreau

David Charles McConnell

Weilong Zhang

Michael A Kryzman

Teresa Kruckenberg

Diana Giulietti

John S Linck

Xiaolan Hu

Barbara M Peyton

John D Edquist

Ricardo O Brown

David P McConnell

Leslie Scotte Steele

Timothy R Boysen

Weiming Lu

William R Fiske

Michael E Folsom

David J Grulke

Anthony Santiago

Kevin R Bordage

Jun Nable

Jorge Ramon Mesa

Iwona Wrobel

Callie Lynn Benson

Lara Naomi Huapaya Rojas

David L Rose

Brian K Orwig

Philip Sheehan

Krystyna Kapalczynski

John Weaver

David Mcconnell

David C Mcconnell

Irene W Rexwinkle

David Charles Mcconnell

An oxidation protection system disposed on a substrate is provided, which may comprise a boron layer comprising a boron compound disposed on the substrate; a silicon layer comprising a silicon compound disposed on the boron layer; and at least one sealing layer comprising monoaluminum phosphate and phosphoric acid disposed on the silicon layer.

High temperature oxidation protection for composites

An air inlet section for an aircraft propulsion system nacelle includes an outer skin, an inner skin, and a lip skin. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The lip skin forms an exterior lip skin surface extending from the inner end to the outer end. The exterior lip skin surface forms a leading edge of the lip skin. The exterior lip skin surface includes an outer surface portion and an inner surface portion. The outer surface portion extends from the outer end to the inner surface portion. The outer surface portion forms a hydrophobic surface. The inner surface portion extends from the inner end to the outer surface portion. The inner surface portion forms a hydrophilic surface.

Lip skin with hydrophobic and hydrophlic surfaces for an aircraft aerostructure

Disclosed is a phosphate coating, comprising: a phosphate portion, wherein the phosphate portion comprises pores, wherein the pores are at least partially filled with a corrosion inhibition sealant, wherein the corrosion inhibition sealant comprises: a base, wherein the base comprises a matrix and a metal within the matrix, wherein the metal within the matrix comprises aluminum, an aluminum alloy, zinc, a zinc alloy, magnesium, a magnesium alloy, or a combination thereof and an inhibitor mixed within the base, wherein the inhibitor comprises zinc molybdate, magnesium metasilicate, trivalent chromium, tungstenate, a metal phosphate silicate, or a combination thereof.

Phosphate coating which can be substantially free of hexavalent chromium and methods of making the same

Disclosed are methods for quantifying the cleanability of a surface of an article, for instance an aircraft interior component. In embodiments, a solution containing an artificial 'dirt' is introduced to a surface under test to simulate a sullied condition. The sullied surface is subjected to at least one cleaning process. Obtained reference and post-cleaning light measurements are compared to determine a measurement difference corresponding to a cleanability of the surface and/or effectiveness of the at least one cleaning process. In embodiments, the measurement difference is assigned a cleanability score for at least one of determining a passing or failing cleanability, modifying the cleaning process, indicating the need for a second or subsequent cleaning, modifying the barrier coating formulation, redesigning the article, etc. The disclosed methods provide solutions for objective verification measures of surface cleanability used to facilitate new article designs, materials, barrier coatings, cleaning processes, cleaners, etc.

Methods for measuring and quantifying surface cleanability of articles

Systems and methods for forming an oxidation protection system on a composite structure are provided. In various embodiments, the oxidation protection system comprises a boron-glass layer formed on the composite substrate and a silicon-glass layer formed over the boron-glass layer. Each of the boron-glass layer and the silicon-glass layer includes a glass former.

Oxidation protection with improved water resistance for composites

Disclosed are pigmented multifunctional barrier coating compositions for application to components such as aircraft interior components. In embodiments, compositions include a base coating component in an amount from 5 to 40 weight percent of the composition, a solvent in an amount from 50 to 70 weight percent of the composition, and at least two performance components from an FST-resistive component in an amount from 0.1 to 5 weight percent of the composition, a UV-resistive component in an amount from 0.1 to 2 weight percent of the composition, an antimicrobial component in an amount from 0.1 to 5 weight percent of the composition, and a dye component in an amount less than 0.5 weight percent of the composition. The composition further includes pigment in an amount up to 10 weight percent of the composition for imparting a cosmetic appearance to the component such as a metallic appearance.

Pigmented multifunctional barrier coating compositions

Disclosed are methods for detecting an antimicrobial surface coating on a substrate including the steps of applying an anionic agent to a surface of the substrate, allowing the anionic agent to bond to antimicrobial surface coating present on the substrate, removing unbonded anionic agent, subjecting the surface of the substrate to a predetermined process to effect a change in the bonded anionic agent, observing the change, and verifying, based on the observed change, the presence of antimicrobial surface coating on the substrate. Further disclosed are antimicrobial surface coating solutions, methods for their application, and methods for reactivated antimicrobial surface coatings.

Antimicrobial surface coating formation, detection, quantification and reactivation systems and methods

A method includes depositing an antimicrobial material onto a surface of a substrate. The method includes binding a photochromic material to the antimicrobial material. Depositing the antimicrobial material and binding the photochromic material can include forming a mixture of the antimicrobial material and the photochromic material and depositing the mixture onto the surface of the substrate. It is also contemplated that depositing the antimicrobial material and binding the photochromic material can include first depositing the antimicrobial material onto the surface of the substrate and then depositing the photochromic material onto the antimicrobial material.

Detecting antimicrobial surfaces

Systems and methods for forming an oxidation protection system on a composite structure are provided. In various embodiments, the oxidation protection system comprises a boron-glass layer formed on the composite substrate and a silicon-glass layer formed over the boron-glass layer. Each of the boron-glass layer and the silicon-glass layer include a glass former and a glass modifier. The boron-glass layer includes a boron compound comprising a mixture of boron carbide (BC) powder and cubic boron nitride (BN) powder.

Oxidation protection of composites

A method of manufacture can comprise: treating a surface of a polymeric substrate with a laser induced graphene; and bonding a metallic layer to the laser induced graphene.

Laser induced graphene as pretreatment to plate non-conductive composites

A method for forming an oxidation protection system on a composite structure are provided. The method includes applying a composite slurry to the composite structure, wherein the composite slurry comprises boron carbide, silicon carbide, borosilicate glass, an oxygen reactant compound including a silica forming component, and a carrier fluid and heating the composite structure to a temperature sufficient to form a boron-silicon-glass-oxygen reactant layer on the composite structure.

A method of forming an adhesively bonded structure may comprise applying a primer compound to a first substrate, wherein the primer compound comprises a functionalized nanomaterial dopant, drying the primer compound on the substrate to form a primer layer comprising the functionalized nanomaterial dopant, applying an adhesive compound over the primer layer to form an adhesive layer, wherein the adhesive compound comprises the functionalized nanomaterial dopant, contacting the adhesive layer with a second substrate and curing the adhesive layer to form an adhesively bonded structure, wherein the first substrate is metallic and the second substrate is at least one of metallic or composite.

Corrosion inhibition system primers and adhesives for metal bond structures

An air management system of a vehicle having a conditioned area includes at least one duct defining a flow path for delivering air to the conditioned area and a sterilization system associated with the at least one duct. The sterilization system including at least one light source operable to emit a germicidal ultraviolet light into the flow path defined by the at least one duct to sterilize the air to be provided to the conditioned area.

Integration of UV light into aircraft air management systems

A method can include vapor depositing a corrosion resistant coating to internal and external surfaces of a metallic air data probe. For example, vapor depositing can include using atomic layer deposition (ALD). The method can include placing the metallic air data probe in a vacuum chamber and evacuating the vacuum chamber before using vapor deposition. The corrosion resistant coating can be or include a ceramic coating. In certain embodiments, vapor depositing can include applying a first precursor, then applying a second precursor to the first precursor to form the ceramic coating.

Air data probe corrosion protection

An air management system of a vehicle having a conditioned area includes at least one duct defining a flow path for delivering air to the conditioned area and a filter arranged within the at least one duct upstream from the conditioned area. The filter includes a filter media having at least one filter media layer including a plurality of fibers. A coating is applied to at least a portion of the plurality of fibers and the coating is operable to deactivate a microbe arranged in contact with the coating.

Aircraft air management systems for deactivating contaminants

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Ashland, MA, United States of America

Steven A Poteet