- 专利标题： Turbomachine blade cooling circuit
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申请号： US16314341申请日： 2017-06-07
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公开(公告)号： US10682687B2公开(公告)日： 2020-06-16
- 发明人: Coralie Cinthia Guerard , Vincent Marc Herb , Jun Ni , Joseph Toussaint Tami Lizuzu , Matthieu Jean Luc Vollebregt
- 申请人： SAFRAN AIRCRAFT ENGINES
- 申请人地址： FR Paris
- 专利权人： SAFRAN AIRCRAFT ENGINES
- 当前专利权人： SAFRAN AIRCRAFT ENGINES
- 当前专利权人地址： FR Paris
- 代理机构： Christensen O'Connor Johnson Kindness PLLC
- 优先权： com.zzzhc.datahub.patent.etl.us.BibliographicData$PriorityClaim@afd97bf
- 国际申请： PCT/FR2017/051438 WO 20170607
- 国际公布： WO2018/002466 WO 20180104
- 主分类号： B22C9/10
- IPC分类号： B22C9/10 ; B22C9/24 ; F01D5/18 ; B22C9/04
摘要：
The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.
公开/授权文献
- US20190240725A1 TURBOMACHINE BLADE COOLING CIRCUIT 公开/授权日：2019-08-08
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