Method for bonding a turbine engine vane segment
US5732468A · kind A · utility
30Cited by
10References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 5, 1996 |
| Grant date | Mar 31, 1998 |
| Priority date | — |
| Expiry date | Dec 5, 2016 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
An airfoil and a band or platform member of a vane segment, such as of a turbine engine, are bonded at a non-linear clearance slot formed between a shelf in the band and an end and edge of the airfoil. A reservoir bead of a bonding alloy slurry is deposited at one slot opening, a metallic powder is packed into the slot, and another reservoir bead is applied at a slot second opening substantially to close the slot and entrap the powder therein. Then the reservoir beads and powder are heated to flow material of the beads into the clearance slot. This bonds the airfoil and band securely at a deep pocket or blind slot.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.