Honeywell International Inc.

Richard Rateick

Dinkar A Mylaraswamy

Larry A Portolese

Emmanuel Obiesie Nwadiogbu

William Scott Rowan

Gary Valencourt

Andrew Peter Vechart

Donna Laboda

Daniel J Laboda

Mark E Behnke

Christopher Gedeon

Giles Horban

Matthew Brown

A vibration-resistant, flexible metallic seal for use in an electrohydraulic servo valve (EHSV), the EHSV comprising an armature, an armature support comprising a base, and a flapper, the seal surrounding a portion of the flapper, the seal having a first end, a second end, a thickness along a length of the seal between the first end and the second end, the thickness being defined between first and second outer surfaces of the seal, and one or a plurality of convolutions between the first end and the second end, the first end disposed between and hermetically connected to the flapper and the armature, the second end disposed within the first opening and hermetically connected to the base, wherein the seal comprises: a non-porous metal that comprises a first fraction of the thickness; a porous metal comprising a plurality of pores that comprises a second fraction of the thickness; and an elastomeric material encompassed by the pores of the second fraction of the thickness, wherein the second fraction comprises one or both of the first and second outer surfaces of the seal.

Electrohydraulic valve including a vibration-resistant, flexible hermetic seal

An in-line continuous flow liquid-gas separator-pump includes a housing, a rotor, a plurality of tubular flow passages, and a plurality of gas flow passages. The rotor includes a rotor first end, a rotor second end, an outer surface, and an inner surface that defines an inner chamber in fluid communication with the purge gas outlet. The tubular flow passages are formed in the rotor and extend between the rotor first end and the rotor second end. Each tubular flow passage includes a fluid inlet that is disposed adjacent the rotor first end and in fluid communication with the liquid/gas inlet, and a fluid outlet that is disposed adjacent the rotor second end and is in fluid communication with the liquid outlet. The gas flow passages are formed in the rotor, and each provides fluid communication between one of the tubular flow passages and the inner chamber.

In-line continuous flow liquid-gas separator-pump

The exposure of an aircraft component to an oxidation catalyst, such as a deicing solution, may be detected with the aid of an electrical conductivity sensor. In some examples, a system includes an aircraft component, an electrical conductivity sensor mechanically connected to the aircraft component and configured to generate an output, and a processor configured to detect an oxidation catalyst exposure event based on the output generated by the electrical conductivity sensor. The electrical conductivity sensor may be configured and positioned to generate a signal indicative of electrical conductivity of a substance to which the aircraft component is exposed. The processor may be configured to detect an oxidation catalyst exposure event by at least determining whether the electrical conductivity indicated by the signal is greater than or equal to a predetermined conductivity threshold value.

Oxidation catalyst detector for aircraft components

A system method of estimating health of aircraft brake system friction material includes sensing a temperature of the friction material, and supplying the sensed temperature to a processor-implemented thermal model that is configured to estimate friction material temperatures at one or more locations on the friction material. The estimates of friction material temperatures are supplied to a processor-implemented thermal oxidation model that is configured, based on the estimates of friction material temperatures, to estimate friction material loss due to thermal oxidation. Data representative of runway fluid exposure are supplied to a processor-implemented catalytic oxidation model that is configured, based on the runway fluid exposure, to estimate friction material loss due to catalytic oxidation. The health of the friction material is estimated based on the estimates of friction material loss from the processor-implemented thermal oxidation model and the processor-implemented catalytic oxidation model.

Aircraft brake health monitoring system and method

Methods and apparatus are provided for lubricating a piston-to-shoe interface in a hydraulic motor or pump. Piston assemblies are installed in a housing that are each adapted to receive a reciprocating drive force and are each configured, in response thereto, to cyclically move between an intake direction and a discharge direction. Each piston assembly includes a piston and a piston shoe, and the piston, the piston shoe, or both have a plurality of pockets formed in a surface that defines a piston-to-shoe interface. When the pistons cyclically move, liquid is supplied to each piston-to-shoe interface to form a hydrostatic bearing at each piston-to-shoe interface. A portion of the liquid that is supplied to each piston-to-shoe interface is selectively supplied to and from one or more of the plurality of pockets.

Piston-to-shoe interface lubrication method

A method of producing a piston that involves providing a piston body formed of a first material, the piston body having a cylindrical portion having a diameter, a rounded end, and a neck connecting the rounded end to the cylindrical portion and having a diameter less than the diameter of the piston body, cladding a portion of the cylindrical portion with a first tool steel layer, cladding a portion of the rounded end with a second tool steel layer spaced from the first tool steel layer, heat treating the piston body and nitriding the first and second tool steel layers. Also a piston () having first () and second () nitrided, tool steel clad portions.

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South Bend, IN, United States of America

Richard Rateick