公开(公告)号：CA2568551A1

公开(公告)日：2007-07-18

申请号：CA2568551

申请日：2006-11-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COFFIN CHARLES C ,  TILLMAN THOMAS G ,  WELCH BRIAN M ,  HUANG HE

IPC: F02M33/00 ,  C10G31/11

Abstract: A fuel system for an energy conversion device includes a multiple of non- metallic fuel plates, gaskets, oxygen permeable membranes, porous substrate plates, and vacuum frame plates. Intricate 3-dimension fuel channel structures such as laminar flow impingement elements within the fuel channel dramatically enhan ce oxygen diffusivity in the FSU. The fuel plates are manufactured from a relatively soft non-metallic material. The non-metallic fuel plates and gasket arrangement provide an effective sealing interface between the fuel plate and oxygen permeable membrane, since compression may be applied to the plates without damaging th e relatively delicate oxygen permeable membrane.

公开(公告)号：CA2492998A1

公开(公告)日：2005-07-30

申请号：CA2492998

申请日：2005-01-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPADACCINI LOUIS J ,  HUANG HE ,  LAMM FOSTER PHILIP

IPC: B01D19/00 ,  B01D61/00 ,  B01D67/00 ,  B01D69/02 ,  B01D71/32 ,  C10L1/00 ,  F02C7/00 ,  F02C7/22 ,  F02C7/224 ,  F02C7/232 ,  F02M37/22 ,  B01D65/00 ,  B01D53/22

Abstract: A method for preventing fuel from migrating, i.e., infiltrating, into a mircoporous polymer membrane, such as that used in a fuel deoxygenator devic e of an aircraft to remove dissolved oxygen from the fuel, includes heating the membrane to reduce the size of micropores in the membrane from a first size to a seco nd size that is large enough to allow migration of oxygen through the membrane and small enough to prevent migration of fuel into the membrane. The membrane is an amorphous fluoropolymer on a PVDF substrate and the micropores are reduced i n size by heating the membrane at a temperature between 130.degree.C and 150.degree.C for 2 hours.

公开(公告)号：CA2534158A1

公开(公告)日：2005-03-24

申请号：CA2534158

申请日：2004-09-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KASLUSKY SCOTT F ,  TILLMAN THOMAS G ,  HUANG HE ,  DEVALVE TIMOTHY D ,  BERTUCCIOLI LUCA ,  LAMM FOSTER PHILIP ,  SPADACCINI LOUIS J ,  SABATINO DANIEL R ,  SAHM MICHAEL K ,  BAYT ROBERT L

IPC: B01D19/00 ,  C10L1/00 ,  B01D61/00 ,  B01D63/08 ,  B01D65/08 ,  B01D69/10 ,  B01D69/12 ,  B01D71/32 ,  B01D71/36 ,  F02C7/12 ,  F02C7/14 ,  F02C7/224

Abstract: A system (10) for the management of thermal transfer in a gas turbine engine (14) includes a heat generating sub-system disposed in operable communicatio n with the engine (14), a fuel source (18) configured to supply a fuel, a fuel stabilization unit (16) configured to receive the fuel from the fuel source (18) and to provide the fuel to the engine (14), and a heat exchanger dispos ed in thermal communication with the fuel to effect the transfer of heat from t he heat generating sub-system to the fuel. A method of managing such thermal transfer includes removing oxygen from the fuel in the fuel atabilization un it (16), transferring heat from the heat generating sub-system to the fuel, and combusting the fuel in gas turbine engine (14). System (10) can be used for the thermal management of an aircraft.