Ceramic thermal barrier layer for gas turbine engine component

US6440575B1 · kind B1 · utility

Assignees

• Siemens Aktiengesellschaft · DE
• ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE

Inventors

• Beate Heimberg · Berlin, DE
• Wolfram Beele · Ratingen, DE
• Karl Kempter · Hersbruck, DE
• Ulrich Bast · Birkenfeld, DE
• Thomas Haubold · Erbach, DE
• Michael Hoffmann · Gablingen, DE
• Axel Endriss · Stuttgart, DE
• Peter Greil · Weisendorf, DE
• Chu-Wan Hong · Taichung, TW
• Fritz Aldinger · Rodenbach, DE
• Hans-Jörg Seifert · Stuttgart, DE

Key dates

• Filing date: May 1, 2000
• Grant date: Aug 27, 2002
• Expiry date: May 1, 2020

Classification

• Technology area (CPC C): Chemistry; Metallurgy
• CPC primary: C23C28/00
• WIPO field: Surface technology, coating
• WIPO sector: Chemistry

Abstract

An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.