发明名称 |
Process and refractory metal core for creating varying thickness microcircuits for turbine engine components |
摘要 |
The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion. |
申请公布号 |
US9038700(B2) |
申请公布日期 |
2015.05.26 |
申请号 |
US201213708036 |
申请日期 |
2012.12.07 |
申请人 |
United Technologies Corporation |
发明人 |
Dube Bryan P.;Levy Ryan Shepard;Page Richard H. |
分类号 |
B22C9/00;B22C9/10;B22C9/04;F01D5/18;B22D29/00 |
主分类号 |
B22C9/00 |
代理机构 |
Bachman & LaPointe, P.C. |
代理人 |
Bachman & LaPointe, P.C. |
主权项 |
1. A process of forming a turbine engine component comprising the steps of:
providing only one non-ceramic core formed from a single sheet of refractory metal material; said non-ceramic core providing step comprising providing the single sheet of refractory metal material core having at least one portion for forming at least one as-cast cooling circuit within said turbine engine component; said refractory metal material core providing step comprising machining the single sheet of refractory metal material core into a first portion for forming a serpentine cooling circuit in said turbine engine component and machining a second portion for forming a trailing edge cooling circuit in said turbine engine component, machining said sheet of refractory metal material core into a third portion for forming a leading edge cooling circuit in said turbine engine component, machining said sheet of refractory metal material core into a fourth portion for forming at least one internal cooling passage for said turbine engine component, wherein said first portion is integral to said second, third, and fourth portions; providing a mold having a shape of said turbine engine component; positioning only said non-ceramic core within said mold; introducing a molten metal material into said mold and allowing said molten metal material to solidify and form said turbine engine component; and removing said non-ceramic core from said solidified turbine engine component. |
地址 |
Hartford CT US |