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.

公开(公告)号：EP1677888A4

公开(公告)日：2008-12-17

申请号：EP04783422

申请日：2004-09-08

Applicant: UNITED TECHNOLOGIES CORP

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

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

CPC classification number: B01D69/10 ,  B01D19/0031 ,  B01D61/00 ,  B01D63/082 ,  B01D63/084 ,  B01D65/08 ,  B01D2321/2008 ,  F02C7/12 ,  F02C7/14 ,  F02C7/224 ,  Y02T50/672 ,  Y02T50/675

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 communication 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 disposed in thermal communication with the fuel to effect the transfer of heat from the heat generating sub-system to the fuel. A method of managing such thermal transfer includes removing oxygen from the fuel in the fuel atabilization unit (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.