MICRO-LATTICE CROSS-FLOW HEAT EXCHANGERS FOR AIRCRAFT

• Main Authors: VANNICE, WILLIAM, KUSUDA, CHARLES E, MULEY, ARUN, MALONEY, KEVIN JOHN, ROPER, CHRISTOPHER STEPHEN
• Format: Patent
• Language: English; French
• Published: 30.05.2017
• Subjects: AEROPLANES; AIRCRAFT; ARRANGEMENTS OR ADAPTATIONS OF HEATING, COOLING, VENTILATING,OR OTHER AIR-TREATING DEVICES SPECIALLY FOR PASSENGER OR GOODSSPACES OF VEHICLES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; BLASTING; COSMONAUTICS; DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; HEAT EXCHANGE IN GENERAL; HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT; HEATING; HELICOPTERS; LIGHTING; MECHANICAL ENGINEERING; PARACHUTES; PERFORMING OPERATIONS; TRANSPORTING; VEHICLES IN GENERAL; WEAPONS

An aircraft micro-lattice cross-flow heat exchanger and methods are presented. A first aircraft fluid source inlet provides a first fluid from a first aircraft system, and a second aircraft fluid source inlet provides a second fluid from a second aircraft system. A structural body supports aviation induced structural loads and exchanges heat between the first fluid and the second fluid. The structural body comprises hollow channels forming two interpenetrating fluidically isolated volumes that flow the first fluid within the hollow channels and flow the second fluid external to the hollow channels isolated from the first fluid. The hollow channels comprise a hollow three-dimensional micro-truss comprising hollow truss elements extending along at least three directions, and hollow nodes interpenetrated by the hollow truss elements. Linvention décrit un échangeur de chaleur double flux à microtreillis pour avion et des procédés. Une première entrée de source de fluide pour avion offre un premier fluide provenant dun premier système davion, et une seconde entrée de source de fluide pour avion offre un second fluide provenant dun second système davion. Un corps structural soutient des charges structurales induites par laviation et échange de la chaleur entre le premier fluide et le second fluide. Le corps structural comprend des canaux creux formant deux volumes isolés de manière fluide interpénétrant qui écoulent directement le premier fluide à lintérieur des canaux creux et écoulent le second fluide externe aux canaux creux isolés du premier fluide. Les canaux creux comprennent un microtreillis creux en trois dimensions comprenant des éléments de treillis creux sétendant le long dau moins trois directions, et des nuds creux interpénétrés par les éléments de treillis creux.