EP 3956547 B1 20230607 - SPLITTER FOR A TURBOFAN ENGINE
Title (en)
SPLITTER FOR A TURBOFAN ENGINE
Title (de)
SCHNABEL FÜR EINE FLUGGASTURBINE
Title (fr)
BEC DE SEPARATION DE TURBOMACHINE AERONAUTIQUE
Publication
Application
Priority
- FR 1904065 A 20190416
- EP 2020060453 W 20200414
Abstract (en)
[origin: WO2020212344A1] The invention relates to a nozzle (1) for separating a primary flow from a secondary flow in a double-flow turbomachine. The separation nozzle comprises an outer annular wall (12), an inner annular wall (13), a radial annular wall (14) and an inner annular baffle (16), and defines a first cavity (17) between the outer annular wall (12) and the inner annular baffle (16), and a second cavity (18) between the inner annular wall (13), the radial annular wall (14) and the inner annular baffle (16).
IPC 8 full level
F01D 25/00 (2006.01); F01D 25/02 (2006.01)
CPC (source: EP US)
F01D 9/02 (2013.01 - US); F01D 25/00 (2013.01 - EP); F01D 25/02 (2013.01 - EP US); F05D 2220/323 (2013.01 - US); F05D 2230/30 (2013.01 - EP); F05D 2230/31 (2013.01 - US); F05D 2230/53 (2013.01 - EP); F05D 2240/10 (2013.01 - EP); F05D 2240/128 (2013.01 - US)
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
DOCDB simple family (publication)
WO 2020212344 A1 20201022; CN 113795650 A 20211214; CN 113795650 B 20230407; EP 3956547 A1 20220223; EP 3956547 B1 20230607; FR 3095230 A1 20201023; FR 3095230 B1 20210319; US 11982195 B2 20240514; US 2022205366 A1 20220630
DOCDB simple family (application)
EP 2020060453 W 20200414; CN 202080034311 A 20200414; EP 20716855 A 20200414; FR 1904065 A 20190416; US 202017604170 A 20200414