<p>A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn. A method of casting the component and a method of using the component are disclosed.</p>
申请公布号
WO2014163698(A1)
申请公布日期
2014.10.09
申请号
WO2013US77966
申请日期
2013.12.27
申请人
VANDERVAART, PETER L.;RHODES, JEFFREY F.;KWON, OKEY;HEFFERNAN, TAB M.
发明人
VANDERVAART, PETER L.;RHODES, JEFFREY F.;KWON, OKEY;HEFFERNAN, TAB M.