公开(公告)号：AU2002242188A1

公开(公告)日：2002-09-04

申请号：AU2002242188

申请日：2002-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LENTS CHARLES E ,  SAHM MICHAEL K ,  WELCH RICHARD C ,  ALBERO JOSE

IPC: B64D13/06 ,  F02C7/32 ,  F02D41/22

Abstract: The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system. The aircraft also includes an auxiliary power unit for supplying electrical power to at least the first motor drive for initiating operation of the first engine.

公开(公告)号：DE60317118T2

公开(公告)日：2008-07-31

申请号：DE60317118

申请日：2003-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GLAHN J AXEL ,  SAHM MICHAEL K

IPC: B64D41/00 ,  B64D33/02 ,  B64D33/04 ,  F02C3/13 ,  F02C7/27 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F02K3/077

Abstract: The present invention relates to an engine integrated auxiliary power unit. The engine (10) comprises a high pressure spool which includes a high pressure compressor (20) connected to a high pressure turbine (22) and a low pressure spool which includes a low pressure compressor (12) connected to a low pressure turbine (14). The engine further has a system for independently operating the high pressure spool and thus allowing the high pressure spool to function as an auxiliary power unit.

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：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：CA1275052A

公开(公告)日：1990-10-09

申请号：CA526017

申请日：1986-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SAHM MICHAEL K ,  MILANO ROBERT

IPC: F01D5/18 ,  F01D9/02

Abstract: Convergent-Divergent Film Coolant Passage A coolant passage through a wall to be cooled, such as the wall of a hollow airfoil, is shaped and oriented to eject coolant fluid therefrom within the boundary layer of hot gases flowing over the surface to film cool the wall downstream of the outlet. The passage includes a metering portion near its inlet, followed by a diffusing portion and nozzle portion. The nozzle portion, adjacent the outlet, simultaneously diverges and converges in mutually perpendicular directions to produce a more uniform coolant velocity profile, which results in increased coolant area coverage and improved cooling effectiveness.