公开(公告)号：US09920638B2

公开(公告)日：2018-03-20

申请号：US14320911

申请日：2014-07-01

Applicant: SNECMA

Inventor： Son Le Hong ,  Gael Frédéric Claude Cyrille Evain ,  Didier Fabre ,  Philippe Picot

IPC: F01D5/30 ,  F04D29/02 ,  F04D29/26 ,  F04D29/32

CPC classification number: F01D5/3084 ,  F01D5/3023 ,  F01D5/3069 ,  F04D29/023 ,  F04D29/26 ,  F04D29/321 ,  F04D29/322 ,  F05D2230/22 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.