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公开(公告)号:US20150308273A1
公开(公告)日:2015-10-29
申请号:US14542209
申请日:2014-11-14
发明人: James S. Perron , William C. Baker , Derek A. Rice
CPC分类号: F01D5/02 , B23K20/002 , B23K20/02 , B23K20/24 , B23K31/02 , C25D5/02 , F01D5/286 , F01D5/3061 , F01D5/3069 , F01D5/34 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/236 , F05D2230/31 , F05D2230/40 , F05D2230/60 , F05D2230/90 , F05D2260/941 , F05D2260/96 , F05D2300/14 , F05D2300/143 , F05D2300/607 , Y10T29/4932 , Y10T29/49321 , Y10T29/49336
摘要: A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.