EP 2167798 A2 20100331 - TURBOJET ENGINE FOR AIRCRAFT
Title (en)
TURBOJET ENGINE FOR AIRCRAFT
Title (de)
TURBOSTRAHLTRIEBWERK FÜR EIN FLUGZEUG
Title (fr)
TURBOREACTEUR POUR AERONEF
Publication
Application
Priority
- FR 2008051089 W 20080618
- FR 0755988 A 20070625
Abstract (en)
[origin: WO2009007564A2] The invention relates to a turbojet engine for an aircraft that comprises an engine provided in a nacelle and at least one heat exchanger (13) for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting said partially-cooled hot flow into said propulsion system, characterised in that at least one heat exchanger (13) is a radial heat exchanger extending in the lower portion of the turbojet engine at a lower branching (16) of the turbojet engine.
IPC 8 full level
CPC (source: EP US)
F01D 9/065 (2013.01 - EP US); F02C 7/14 (2013.01 - EP US); F02C 7/185 (2013.01 - EP US); F02K 3/06 (2013.01 - EP US); F02K 7/14 (2013.01 - EP US); F05D 2240/12 (2013.01 - EP US); F05D 2250/32 (2013.01 - EP US); F05D 2260/20 (2013.01 - EP US); F05D 2260/2214 (2013.01 - EP US); F28D 2021/0021 (2013.01 - EP); Y02T 50/60 (2013.01 - EP US)
Citation (search report)
See references of WO 2009007564A2
Designated contracting state (EPC)
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR
Designated extension state (EPC)
AL BA MK RS
DOCDB simple family (publication)
FR 2917714 A1 20081226; FR 2917714 B1 20091127; BR PI0812818 A2 20141209; CA 2690601 A1 20090115; CN 101730791 A 20100609; EP 2167798 A2 20100331; JP 2010531408 A 20100924; RU 2010102057 A 20110727; RU 2471682 C2 20130110; US 2010300066 A1 20101202; WO 2009007564 A2 20090115; WO 2009007564 A3 20090430
DOCDB simple family (application)
FR 0755988 A 20070625; BR PI0812818 A 20080618; CA 2690601 A 20080618; CN 200880021702 A 20080618; EP 08806024 A 20080618; FR 2008051089 W 20080618; JP 2010514052 A 20080618; RU 2010102057 A 20080618; US 66579008 A 20080618