公开(公告)号：US20170136534A1

公开(公告)日：2017-05-18

申请号：US15323766

申请日：2015-06-29

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Francois CASTEILLA ,  Sebastien DIGARD BROU DE CUISSART ,  Serge FARGEAS ,  Vincent HERB

IPC分类号： B22D25/02 ,  B22C9/10 ,  B22C9/24 ,  F01D5/18 ,  B22D29/00 ,  B22D30/00 ,  F01D5/14 ,  B22C1/00 ,  B22D21/00

CPC分类号： B22D25/02 ,  B22C1/00 ,  B22C9/108 ,  B22C9/24 ,  B22D19/00 ,  B22D19/04 ,  B22D21/005 ,  B22D29/001 ,  B22D30/00 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/284 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2300/177 ,  F05D2300/211 ,  Y02T50/676

摘要： A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.