The Boeing Company

Christopher Mark Severns

Mark Eugene Liffring

Kamiar J Karimi

Thomas F Currier

Ty Aaby Larsen

Andrew Johnson

George Michael Roe

Mark Stephen Shander

Robert Dennis Holley

David S Krug

Mark William Lesyna

Andrew John Bayliss

John Ralph Hull

Vyacheslav Khozikov

Robert Thomas Johnson

Jian Huang

Todd Burton Brouwer

Thomas R Hasenoehrl

Terrance L Thomas

John T Paterson

Alan Thomas Bernier

Lowell W Schaffner

Jon J Dhondt

Margaret Douglas

Vikram D Immanuel

Ronald C Yabut

Seth C Tai

Robert D Holley

Mark S Shander

Todd B Brouwer

A system for acoustically detecting dielectric breakdown of, or partial discharge within, or on, an electrical device includes at least one electroacoustic (EA) transducer configured to detect an acoustic vibration of the electrical device, and a controller electrically connected to the at least one EA transducer. The controller is configured to receive a signal from the at least one EA transducer, and analyze the signal to determine whether the signal includes data associated with an acoustic vibration in a frequency range of dielectric breakdown and/or partial discharge of the electrical device. The applicability of such a system includes, but is not limited to, electronic parts or assembly screening, life characterization testing for materials and processes, diagnostic methods or aides, augmenting testing of components, assemblies or systems, and in service monitoring to support preventative or condition based maintenance to avert an in-service issues.

Systems and methods for acoustically detecting dielectric breakdown and partial discharge events in electrical devices

An electrical system is provided. The electrical system includes an insulated electrical conductor installed in an aircraft and configured to conduct a current over a length of the insulated electrical conductor. The electrical system includes an optical fiber includes a jacket surrounding an optical core, the optical fiber installed adjacent to the insulated electrical conductor. The electrical system includes a photo detector coupled to the optical fiber and configured to detect an electromagnetic signal carried by the optical fiber and at least partially generated as a function of an electrical fault that occurs at a point along the length of the insulated electrical conductor.

Electrical fault detector and method of use

An aircraft may include at least one secondary power system requiring secondary power, at least two main engines, and at least three non-propulsive utility power (NPUP) generation systems. The NPUP generation systems may each be configured to provide full-time secondary power during operation of the aircraft. The NPUP generation systems may be configured to provide at least a portion of the secondary power required by the secondary power system.

Non-propulsive utility power (NPUP) generation system for providing secondary power in an aircraft

A method for generating electrical power comprising operating variable frequency generators using a common prime mover and controlling the variable frequency generators using a mechanical phase difference as follows: wherein MPD is the mechanical phase difference in degrees between rotors between a pair of variable frequency generators, G is a number of variable frequency generators, &#x3a6; is a number of electrical phases in a variable frequency generator in the variable frequency generators, and p is a number of pole pairs in the variable frequency generator in the variable frequency generators, wherein the variable frequency generators are controlled such that each variable frequency generator in the variable frequency generators has a selected mechanical phase difference from another variable frequency generator in the variable frequency generators that is an integer multiple of the mechanical phase difference that is less than 360 degrees.

Electrical power generation system and method for aircraft

Non-propulsive utility power (NPUP) generation system for providing full-time secondary power during operation of an aircraft

A method and apparatus for forming a direct current power supply. An apparatus comprises a transformer and a rectifier. The transformer is figured to output a plurality of phase-shifted alternating currents in response to receiving a plurality of alternating currents. The plurality of alternating currents and the plurality of phase-shifted alternating currents form a plurality of input alternating currents that are offset relative to each other by one-twelfth of a cycle in phase. The rectifier is configured to form a direct current power supply having a common mode voltage reduced to zero within selected tolerances in response to receiving the plurality of input alternating currents.

Six-phase supplied transformer rectifier unit

A modular truss assembly configured to be placed in small or narrow spaces such as within the floor, sidewall, or crown of a vehicle for mechanically and electrically mounting system components of a modular equipment center (MEC). A plurality of MECs is spatially distributed throughout the vehicle to service equipment loads. The modular truss assembly provides different voltage levels for powering the system components of the MEC and for powering the equipment loads. In one or more configurations, all or part of the modular truss assembly can be removed from the vehicle for repair or replacement.

Modular equipment center distributed equipment packaging truss

Distributed electronic protections and control architecture enabling simultaneous fault clearance without conflicting fault isolation logic. A plurality of modular equipment centers (MECs) is spatially distributed throughout a vehicle to service equipment loads with power and data. In one embodiment, protective functions are embedded on integrated protection chipsets (IPCs) within the distributed architecture of the vehicle. The IPCs implement a plurality of protective functions where coordinated or independent fault assessments are performed.

Modular equipment center distributed independent protections

A modular truss assembly for mechanically and electrically mounting system components of a modular equipment center (MEC). A plurality of MECs is spatially distributed throughout the vehicle to service equipment loads. The modular truss assembly provides different voltage levels for powering the system components of the MEC and for powering the equipment loads. In one or more configurations, a MEC incorporate inductive power coupling for powering a line replaceable unit (LRU) in proximity to the modular truss assembly without exposed electrical connections and such that the MEC may forgo power conversion equipment. In one or more configurations, a sensor is embedded in one or more transfer layers of the truss for measuring a power trace embedded in the modular truss assembly.

Modular equipment center integrated truss sensors

Growing community of inventors

Issaquah, WA, United States of America

Christopher Mark Severns