A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity in a support structure, inserting a flared end of a vane in the oversized cavity, and inserting a wedge for mechanically retaining the flared end of the vane in
A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity in a support structure, inserting a flared end of a vane in the oversized cavity, and inserting a wedge for mechanically retaining the flared end of the vane in the oversized cavity.
대표청구항▼
What is claimed is: 1. A method which comprises the steps of forming a pinched oversized cavity having a pinched end and a large end in a support structure, inserting a flared end of a vane into said oversized cavity through said pinched end so that a first side of said flared end of said vane abut
What is claimed is: 1. A method which comprises the steps of forming a pinched oversized cavity having a pinched end and a large end in a support structure, inserting a flared end of a vane into said oversized cavity through said pinched end so that a first side of said flared end of said vane abuts a first interior edge of the cavity and a second side of said flared end of said vane is spaced from a second interior edge of the cavity, and inserting means for mechanically retaining said flared end of said vane in said oversized cavity through said large end of said cavity so that said mechanical retaining means abuts said second interior edge of said cavity and said second side of said flared end and so that an outer edge of said mechanical retaining means is flush with an outer edge of said support structure. 2. The method according to claim 1, wherein said forming step comprises forming a cavity having a larger dimension adjacent said outer edge of said support structure and a smaller dimension adjacent an inner edge of said support structure. 3. The method according to claim 2, wherein said inserting step comprises installing a wedge detail between a wall of said cavity and a wall of said flared end of said vane. 4. The method according to claim 3, wherein said installing step comprises installing said wedge detail into said large end of said cavity having said larger dimension. 5. The method of claim 1, further comprising applying an adhesive to walls of said cavity, walls of said flared end, and walls of said mechanical retention means so as to secure said flared end of said vane and said mechanical retention means to said side walls of said cavity and said support structure. 6. A turbine engine component comprising a support structure, a cavity within said support structure, said cavity having a first interior wall and a second interior wall, an airfoil surface having a flared end positioned within said cavity, said flared end having a first side which abuts said first interior wall and a second side which is spaced from said second interior wall and forms a gap with said second interior wall, and means positioned within said cavity for mechanically retaining said end of said at least one airfoil surface within said cavity, said mechanical retaining means being positioned within said gap and having a first side wall which abuts said second side of said flared end and a second side wall which abuts said second interior wall, and said mechanical retaining means further having an outer edge which is flush with an outer edge of said support structure when said mechanical retaining means is positioned within said gap. 7. The turbine engine component of claim 6, wherein said support structure has an inner edge and said cavity has a larger dimension adjacent said outer edge and a smaller dimension adjacent said inner edge and said cavity being larger than said flared end. 8. The turbine engine component of claim 7, wherein said mechanical retaining means comprises a wedge detail positioned between a side wall of said cavity and a wall of said flared end and said wedge detail has an outer edge which is flush with said outer edge of said support structure and an inner edge which is flush with said inner edge of said support structure. 9. The turbine engine component of claim 8, wherein said vane, wedge and support structure are formed from non-metallic materials. 10. The turbine engine component of claim 8, wherein said wedge detail is formed from a non-metallic material selected from the group consisting of polyurethane, a high performance, glass fiber reinforced engineering composite molding compound, nylon, and a polyetherimide material. 11. The turbine engine component of claim 8, wherein said wedge detail has said outer edge, an inner edge, said first side wall connecting said outer edge and said inner edge, and said second side wall connecting said outer edge and said inner edge, and said first and second side walls forming a taper angle in the range of from 3.0 to 7.0 degrees. 12. The turbine engine component of claim 8, further comprising an adhesive material for joining said wedge detail to said flared end, for joining said flared end to said support structure, and for joining said wedge detail to said support structure. 13. The turbine engine component according to claim 6, wherein said component comprises an outlet guide vane. 14. The turbine engine component according to claim 6, wherein said support structure comprises an outer base of an outlet guide vane, said outlet guide vane has an inner base and said vane extends between said inner base and said outer base. 15. A wedge detail for use in replacing or repairing turbine engine components, said wedge detail being formed from a non-metallic material and having a first side wall and a second side wall forming a taper angle in the range of from 3.0 to 7.0 degrees with respect to said first side wall.
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이 특허에 인용된 특허 (3)
Murphy Guy C. (Fairfield OH) Haaser Frederic G. (Cincinnati OH) Matacia Anthony J. (Cincinnati OH), Gas turbine outlet guide vane mounting assembly.
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