The Boeing Company

Hrl Laboratories, LLC

Charles Edward Kusuda

Arun Muley

Christopher Stephen Roper

Thomas R Hasenoehrl

David Page

Randall C Schubert

Namsoo Paul Kim

John Charles Gray

Erik L Godo

Christopher J Ro

Leigh M Sedgwick

Jeffrey W Glasnovich

Quy Lam

Theodore M Barry

Roy D Nye

William Vannice

Kevin John Maloney

Scott M Satterfield

John D Blake

A condenser having passages of varying geometry for cooling of fluid. The condenser apparatus includes substantially parallel tubes each defining a channel and having an inlet at a first end and an outlet at a second end, the first end having a greater hydraulic diameter than the second end. Inlet and outlet manifolds are provided. The tubes may be oriented substantially vertically with the inlets above the respective outlets. A heat exchanger core comprises the tubes and substantially horizontally oriented fin material connecting the tubes. The tubes may receive a relatively higher temperature vapor or vapor and liquid mixture into the inlets of the tubes, around the tubes coolant flows substantially horizontally to remove heat from the tubes, and relatively cooler saturated liquid is discharged from the outlets. In one embodiment, the tube's channel splits into multiple channels to reduce the hydraulic diameter and increase the surface area ratio.

Condenser apparatus and method

A cooling system for use with a power electronics assembly comprising an array of line-replaceable units is provided. The cooling system includes a first manifold coupled in flow communication with the array of line-replaceable units, and a fluid supply coupled in flow communication with the first manifold. The fluid supply is configured to channel cooling fluid towards the first manifold such that the cooling fluid is discharged towards the line-replaceable units in the array substantially simultaneously.

Cooling system for use with a power electronics assembly and method of manufacturing thereof

A heat exchanger with non-circular tubes arranged in a louvered fashion. In one embodiment the tubes include a first plurality of hollow members extending in a first direction, a second plurality of hollow members extending in a second direction different from the first direction, and a third plurality of hollow members extending in a third direction different from the first direction and from the second direction, the hollow members of the first plurality of hollow members, the second plurality of hollow members, and the third plurality of hollow members intersecting at a plurality of hollow nodes.

Louvered elliptical tube micro-lattice heat exchangers

An aircraft including an airframe, a propulsion system, and a heat exchanger is presented. The heat exchanger of the aircraft may include (i) a structural body including a plurality of hollow channels, (ii) a first fluid positioned within the plurality of hollow channels of the structural body, (iii) a plurality of openings positioned on a first side of the structural body and in fluid communication with the plurality of hollow channels, (iv) a wick structure positioned on the first side of the structural body, and further positioned adjacent to an exterior of the plurality of hollow channels and in fluid communication with the plurality of openings, (v) an inlet to the structural body operable to provide a second fluid from an aircraft system, and (vi) an outlet from the structural body operable to receive the second fluid after receiving heat from the first fluid.

Aircraft heat exchanger

A microtruss structure includes a first plane having a first plurality of unit cells. Each of the first plurality of unit cells includes a first plurality of struts and a first node connecting three or fewer struts of the first plurality of struts such that each strut of the first plurality of struts extends through the first node. The microtruss structure also includes a second plane having a second plurality of unit cells. Each of the second plurality of unit cells includes a second plurality of struts and a second node connecting three or fewer struts of the second plurality of struts such that each strut of the second plurality of struts extends through the second node.

Methods and apparatus for a microtruss heat exchanger

In one aspect, conduction cooled modules are described herein. In some implementations, a conduction cooled module comprises first and second external support structures arranged in facing opposition to one another, forming a component envelope therebetween. In some implementations, the modules are configured to contact at least one cold plate and to retain at least one printed wiring board in the component envelope in between the first external support structure and the second external support structure.

Conduction cooled module

A method of manufacturing a heat exchanger including a heat exchanger core of a first material, the method including additive manufacturing a sacrificial scaffold of a second material, the sacrificial scaffold corresponding in shape to that of the heat exchanger core, coating the sacrificial scaffold with a layer of the first material, and removing the sacrificial scaffold to leave behind the heat exchanger core with an integrated self-aligned passage.

Heat exchangers made from additively manufactured sacrificial templates

An aircraft fuselage sidewall may include an aircraft sidewall volume and a flow controller. The aircraft sidewall volume may be delineated by an aircraft skin forming an outboard boundary of the aircraft sidewall volume, a passenger cabin sidewall forming an inboard boundary of the aircraft sidewall volume and fuselage frame structures forming axial boundaries of the aircraft sidewall volume. The flow controller may be positioned at a portion of the aircraft sidewall volume to selectably control air flow through the aircraft sidewall volume.

Method and apparatus for air flow control in an aircraft sidewall volume

A forward in flight entertainment system (IFE) which allows air to be directed to and exhausted from the IFE equipment in isolation from the cabin conditioned air. Further, potential IFE generated smoke may be kept isolated from the cabin air. The forward IFE equipment is located in forward sections of the aircraft system switching from ground to air mode is accomplished through air/ground signal responsive to landing gear truck tilt. Once the air/ground transition from ground mode to air mode has occurred, ventilation valves and will be closed and the heated air will be exhausted overboard by forward IFE cooling overboard valve whose overboard flow increases with altitude and cabin to ambient pressure differential.

Forward in flight (IFE) entertainment cooling system

An aft in flight entertainment system &ldquo;IFE&rdquo; which allows air to be directed to and exhausted from the IFE equipment in isolation from the cabin conditioned air. Further potential IFE generated smoke may be kept isolated from the cabin air. The aft IFE equipment is located in the rear sections of the aircraft. Valves controlling air flow are responsive to input signals. A fan draws cooling air through a video control cabinet through a duct which splits into an overhead branch and an inboard branch.

Growing community of inventors

Mukilteo, WA, United States of America

Charles Edward Kusuda