EP 1913176 A1 20080423 - THERMAL BARRIER COATING SYSTEM
Title (en)
THERMAL BARRIER COATING SYSTEM
Title (de)
WÄRMEDÄMMSCHICHTSYSTEM
Title (fr)
SYSTEME DE COUCHE CALORIFUGE
Publication
Application
Priority
- DE 2006001359 W 20060804
- DE 102005037448 A 20050809
Abstract (en)
[origin: WO2007016906A1] The invention relates to a thermal barrier coating system (11) for components (10), in particular for metal components of a gas turbine such as an aircraft engine, the thermal barrier coating system (11) being formed from a thermal barrier base material. According to the invention, at least one aerogel is incorporated or embedded in the thermal barrier base material.
IPC 8 full level
C23C 28/00 (2006.01); C23C 4/04 (2006.01); F01D 5/28 (2006.01)
CPC (source: EP US)
C23C 4/11 (2016.01 - EP US); C23C 28/042 (2013.01 - EP US); C23C 28/044 (2013.01 - EP US); C23C 28/42 (2013.01 - EP US); C23C 30/00 (2013.01 - EP US); F01D 5/288 (2013.01 - EP US); F05D 2230/90 (2013.01 - EP US); F05D 2300/2118 (2013.01 - EP US); F05D 2300/611 (2013.01 - EP US); F05D 2300/612 (2013.01 - EP US); Y02T 50/60 (2013.01 - EP US)
Citation (search report)
See references of WO 2007016906A1
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
DE 102005037448 A1 20070215; EP 1913176 A1 20080423; US 2009233111 A1 20090917; WO 2007016906 A1 20070215
DOCDB simple family (application)
DE 102005037448 A 20050809; DE 2006001359 W 20060804; EP 06775798 A 20060804; US 98937406 A 20060804