公开(公告)号：US20140308116A1

公开(公告)日：2014-10-16

申请号：US14249489

申请日：2014-04-10

Applicant: ALSTOM Technology Ltd

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

IPC: F01D11/12

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 located in 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.

Abstract translation: 护罩装置热保护具有陶瓷层和金属层的燃气轮机叶片，金属层被陶瓷层热保护，陶瓷层通过具有多个突起的固定装置机械连接到金属层 金属层设计成与位于陶瓷层中的多个空腔接合，使得在环境温度下在空腔和突起之间存在间隙，在燃气轮机的高温运行时，间隙消失，突起为 然后锁定到空腔中。

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.