公开(公告)号：JP2006322458A

公开(公告)日：2006-11-30

申请号：JP2006137181

申请日：2006-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BERTOLOTTI FABIO P ,  LISCINSKY DAVID S ,  SABATINO DANIEL R

IPC: B67D7/74 ,  F02C7/18 ,  F02C6/18 ,  F02K1/28

Abstract: PROBLEM TO BE SOLVED: To optimize mixing characteristic of two fluids crossing in a jet engine part orthogonally. SOLUTION: In an air mixing device for mixing primary fluid with secondary fluid introduced through an opening part of a wall and flowing on a wall face, the opening part has an airfoil shape provided with a leading edge oriented at a certain angle of attack with respect to secondary fluid flow to promote penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening part is selectively positioned to give desired lift for optimizing mixing of two streams by the angle of attack in accordance with the particular application. In one embodiment, a collar is provided around the opening part to prevent secondary fluid from coming into contact with the wall face during certain operation condition. A plurality of opening parts may be used by combination of a large size airfoil-shaped opening part and a small size airfoil-shaped opening part arranged on the downstream side more than it and combination of the airfoil-shaped opening part and a round-shaped opening part arranged on the upstream side more than it. A pair of opening parts and associated collars may be symmetrically arranged to promote mixture in specific application, and a nozzle may be arranged on an inner side of a wall to improve stream characteristic of primary fluid. COPYRIGHT: (C)2007,JPO&INPIT

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：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.