Method for bonding abrasive blade tips to the tip of a gas turbine blade
US5359770A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 8, 1992 |
| Grant date | Nov 1, 1994 |
| Priority date | — |
| Expiry date | Sep 8, 2012 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49337
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
An abrasive system and a processing procedure is provided which permits the direct installation of a thick abrasive blade tip cap onto a cast turbine rotor blade during a heating schedule which requires two furnace operations. The composition of the abrasive blade tip cap advantageously utilizes the high temperature performance capabilities of equiaxed or single crystal rotor blade alloys without significantly affecting their mechanical properties as a consequence of the processing necessary to permanently bond the abrasive blade tip cap to the rotor blade. A semi-rigid mat consisting of the preferred abrasive composition is first consolidated in a first vacuum furnace operation. Blade tip cap preforms are then cut from the mat and positioned on the tip of the rotor blade. The preform and rotor blade are then heated in a vacuum furnace according to a temperature schedule entailing heating rates, holding temperatures and durations which are sufficient to bond the preform to the rotor blade. The rotor blade is then rapidly cooled in the vacuum furnace to retain the microstructure and mechanical properties of the rotor blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.