The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Oct. 11, 2022

Filed:

Oct. 31, 2017
Applicants:

Safran, Paris, FR;

Safran Aircraft Engines, Paris, FR;

Universite Paul Sabatier Toulouse Iii, Toulouse, FR;

Centre National DE LA Recherche Scientifique (Cnrs), Paris, FR;

Inventors:

Aurélien Joulia, Moissy-Cramayel, FR;

André Hubert Louis Malie, Moissy-Cramayel, FR;

Florence Ansart, Lebege, FR;

Elodie Marie Delon, Portet-sur-Garonne, FR;

Sandrine Duluard, Toulouse, FR;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 11/20 (2006.01); C23C 28/00 (2006.01); C04B 41/52 (2006.01); C23C 4/10 (2016.01); C23C 14/08 (2006.01); C04B 41/00 (2006.01); C23C 18/12 (2006.01); F01D 5/28 (2006.01); C04B 41/87 (2006.01); C25D 13/02 (2006.01); C04B 41/50 (2006.01); C04B 41/89 (2006.01); C04B 35/80 (2006.01); C04B 38/00 (2006.01); C04B 111/00 (2006.01);
U.S. Cl.
CPC ...
C23C 28/321 (2013.01); B64C 11/205 (2013.01); C04B 35/80 (2013.01); C04B 38/0051 (2013.01); C04B 41/009 (2013.01); C04B 41/5042 (2013.01); C04B 41/52 (2013.01); C04B 41/87 (2013.01); C04B 41/89 (2013.01); C23C 4/10 (2013.01); C23C 14/083 (2013.01); C23C 18/127 (2013.01); C23C 18/1216 (2013.01); C23C 18/1225 (2013.01); C23C 18/1241 (2013.01); C23C 18/1254 (2013.01); C23C 18/1283 (2013.01); C25D 13/02 (2013.01); F01D 5/28 (2013.01); F01D 5/288 (2013.01); C04B 2111/00405 (2013.01); C04B 2235/522 (2013.01); C04B 2235/526 (2013.01); F05D 2300/6033 (2013.01); F05D 2300/614 (2013.01); F23R 2900/00018 (2013.01);
Abstract

A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.


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