The Boeing Company

David W Kwok

Jack William Mauldin

James Ping Huang

David Michael Smith

Edward L Lawson

John A Weidler

John Anthony Skorupa

Andrew C Kulak

Antonio B Gonzales

John W Smith

Blaine Knight Rawdon

Namsoo Paul Kim

Sang H Nguyen

David M Smith

A method for fuel quantity gauging that measures the quantity of liquid fuel in a fuel tank. The method includes the following steps performed while fuel is flowing out of the fuel tank: changing a volume of gas in the fuel tank (e.g., by injecting or venting gas) during a time interval; measuring a rate of change of the volume of gas in the fuel tank during the time interval; measuring a rate of flow of fuel out of the fuel tank during the time interval; measuring a first pressure and a first temperature of the gas in the fuel tank at the start of the time interval; measuring a second pressure and a second temperature of the gas in the fuel tank at the end of the time interval; and calculating a quantity of fuel in the fuel tank based on the acquired measurement data.

Methods and systems for direct fuel quantity measurement

Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.

Methods and apparatus for supporting engines and nacelles relative to aircraft wings

In one embodiment, a gas turbine engine assembly comprises an engine assembly disposed about a longitudinal axis, a core nozzle positioned adjacent the engine assembly to direct a core flow generated by the engine assembly, a fan nozzle surrounding at least a portion of the core nozzle to direct a fan flow, wherein the core nozzle defines a plenum to receive a portion of the core stream flow from the core nozzle and a thermoelectric generator assembly positioned in the plenum. Other embodiments may be described.

Thermoelectric generator in turbine engine nozzles

Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a first support structure to be coupled to a wing, a second support structure to be coupled to the wing and a nacelle. The support structures are coupled to opposite sides of the nacelle. The support structures are to be coupled to opposite sides of an engine to enable thrust loads to be reacted through the support structures to the wing.

A thermoelectric generator assembly may comprise a frame that may include a first frame member and a second frame member. The first frame member and the second frame member are adapted to retain one or more thermoelectric generator devices in position therebetween for transferring heat energy through the one or more thermoelectric generator devices from a heat source to a heat sink to generate electrical energy. The thermoelectric generator assembly may also include a spacer positioned between the first frame member and the second frame member. A power bus may be included to provide the electrical energy generated by the one or more thermoelectric generator devices for powering an electrical device.

Thermoelectric generator assembly and system

A heat exchanger and associated method are provided that may eliminate or reduce the need for an external mechanical or electrical power source to drive the fan by utilization, instead, of a Stirling engine. A heat exchanger includes a plurality of coils configured to carry a primary fluid. The heat exchanger also includes a fan including a plurality of fan blades configured to force a secondary fluid across the plurality of coils to facilitate heat transfer between the primary and secondary fluids. The heat exchanger also includes a Stirling engine operably connected to the fan and configured to cause rotation of the fan blades. A corresponding method is also provided.

Heat exchanger and associated method employing a stirling engine

A thermoelectric generation system for turbine engines and the like has at least one thermoelectric generator disposed proximate the turbine engine such that waste heat from the turbine engine can be converted into electricity. Vehicle performance and efficiency can be enhanced by mitigating the need for mechanically driven electric power generators, which undesirably drain power from the turbine engine thus adversely affect the vehicle's performance.

Thermoelectric generation system

An airship comprises a shell, a gas storage system, an air storage system, a cargo storage system, a heating system, and a propulsion system. The shell encompasses a volume. The gas storage system is located within the volume, wherein the gas storage system is capable of storing a lighter than air gas. The air storage system is located within the volume, wherein the air storage system is capable of storing heated air. The heating system is capable of heating air. The propulsion system is capable of propelling the shell during flight.

Hybrid thermal airship

A fuel system for an aircraft is disclosed. The fuel system comprises a fuel tank and a fuel reformer for receiving fuel from the fuel tank. The system includes a hydrogen fuel cell array for receiving hydrogen from the fuel reformer. The system further includes mechanism for providing an inerting gas from the fuel system to the fuel tank.

Fuel system for an aircraft including a fuel tank inerting system

A lightning protection system, method and aircraft are provided for reducing the flammability of jet fuel spilled during an in-flight refueling operation between a supplying aircraft and a receiving aircraft. An inert gas is injected adjacent to a refueling interface in order to displace oxygen in the fuel-air mixture and thereby reduce the ability of the fuel vapor to ignite upon occurrence of an ignition source such as lightning. The refueling system may comprise a boom or a hose and drogue type device.

Growing community of inventors

La Mirada, CA, United States of America

David W Kwok