公开(公告)号：US20170002667A1

公开(公告)日：2017-01-05

申请号：US15198915

申请日：2016-06-30

Applicant: Airbus Defence and Space GmbH

Inventor： Juergen STEINWANDEL ,  Ning WANG ,  Helmut PIRINGER

IPC: F01D5/28 ,  B28B11/24 ,  C23C16/30 ,  B28B1/24 ,  C23C16/442 ,  C23C16/04

CPC classification number: F01D5/282 ,  B28B1/24 ,  B28B11/243 ,  C04B35/053 ,  C04B35/117 ,  C04B35/486 ,  C04B35/505 ,  C04B35/62857 ,  C04B35/6286 ,  C04B35/62863 ,  C04B35/62865 ,  C04B35/62894 ,  C04B35/62897 ,  C04B35/6348 ,  C04B35/76 ,  C04B35/803 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/614 ,  C04B2235/616 ,  C23C16/045 ,  C23C16/30 ,  C23C16/32 ,  C23C16/442 ,  F01D5/284 ,  F01D5/288 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/226 ,  F05D2300/228 ,  F05D2300/44 ,  F05D2300/601 ,  F05D2300/6033

Abstract: This relates to a turbine blade comprising a preformed fibrous fabric of fibres consisting of carbon, silicon carbide or rhenium fixed with a binder resin, and wherein the preformed and fixed fibrous fabric is coated and infiltrated, respectively, with B4C, wherein the preformed fibrous fabric that has been fixed and coated and infiltrated, respectively, with B4C further has a multilayer coating consisting of at least one layer of silicon carbide and at least one layer of a metal boride, a metal nitride or a metal carbide, and wherein an oxide ceramic is applied over the multilayer coating. The turbine blade is resistant to high temperatures and is particularly well suited for use in a gas turbine. Methods for producing the turbine blade are also described.

Abstract translation: 这涉及一种涡轮叶片，其包括由碳，碳化硅或铼固定的纤维组成的纤维织物预先形成的纤维织物，所述纤维织物用粘合剂树脂固定，并且其中预先形成的和固定的纤维织物分别用B4C涂覆和渗透，其中预成型纤维织物 已经用B4C分别固定和涂覆和渗透的多层涂层进一步具有由至少一层碳化硅和至少一层金属硼化物，金属氮化物或金属碳化物组成的多层涂层，并且其中氧化物陶瓷 施加在多层涂层上。 涡轮叶片耐高温，特别适用于燃气轮机。 还描述了用于生产涡轮叶片的方法。