公开(公告)号：US09764530B2

公开(公告)日：2017-09-19

申请号：US14250665

申请日：2014-04-11

Applicant: ALSTOM Technology Ltd

Inventor： Gregoire Etienne Witz ,  Matthias Hoebel ,  Hans-Peter Bossmann

IPC: B32B7/08 ,  B23K26/34 ,  B32B18/00 ,  C04B37/02 ,  F23R3/00 ,  B23K26/03 ,  B23K26/211 ,  B23K26/60 ,  B23K26/32 ,  B23K1/19 ,  B23K26/342 ,  B23K103/00 ,  B23K103/16

CPC classification number: B32B7/08 ,  B23K1/19 ,  B23K26/032 ,  B23K26/211 ,  B23K26/32 ,  B23K26/342 ,  B23K26/60 ,  B23K2103/172 ,  B23K2103/52 ,  B32B18/00 ,  C04B37/026 ,  C04B2235/945 ,  C04B2237/12 ,  C04B2237/592 ,  C04B2237/595 ,  C04B2237/64 ,  C04B2237/72 ,  F23M2900/05004 ,  F23R3/007 ,  Y10T428/12618

Abstract: A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

公开(公告)号：US09605555B2

公开(公告)日：2017-03-28

申请号：US14249489

申请日：2014-04-10

Applicant: ALSTOM Technology Ltd ,  Stefan Weber

Inventor： Gregoire Etienne Witz ,  Mathieu Esquerre ,  Michael Stuer ,  Daniel Renusch ,  Hans-Peter Bossmann

IPC: F01D5/20 ,  F01D11/12 ,  F01D9/04

CPC classification number: F01D11/122 ,  F01D9/04 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2300/21

Abstract: Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.