公开(公告)号：CA2554309A1

公开(公告)日：2007-03-07

申请号：CA2554309

申请日：2006-07-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SABATINO DANIEL R ,  SAHM MICHAEL K ,  BAYT ROBERT L ,  KASLUSKY SCOTT

IPC: B64D13/06 ,  B64D13/08 ,  F02C6/04 ,  F02C7/22 ,  F02M31/06

Abstract: A fuel based thermal management system according to the present inventi on includes a fuel stabilization system which permits the fuel to exceed the traditional coking temperatures. An air-to-fuel heat exchanger operates as an environmental control system (ECS) pre-cooler such that the heat from the engine compresso r bleed air is rejected into the fuel to maintain engine operating efficiency.

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：CA2492566A1

公开(公告)日：2005-07-29

申请号：CA2492566

申请日：2005-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPADACCINI LOUIS J ,  BERTUCCIOLI LUCA ,  HUANG HE ,  BAYT ROBERT L

IPC: F02C7/12 ,  F02C3/24 ,  F02C7/18 ,  F02C7/22 ,  F02C7/224 ,  F02C7/141 ,  B01D19/00 ,  B01D61/00 ,  B01D53/22

Abstract: A cooling system for a gas turbine engine includes a fuel deoxygenator f or increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits . The prevention of insoluble deposits increases the usable cooling capacity of th e fuel. The increased cooling capacity of the deoxygenated fuel provides a greater heat sink for cooling air used to protect engine components. The improved cooling capacity of the cooling air provides for increased engine operating temperatures that improves overall engine efficiency.

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.