Abrasive blade tips for cast single crystal gas turbine blades
US5264011A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 8, 1992 |
| Grant date | Nov 23, 1993 |
| Priority date | — |
| Expiry date | Sep 8, 2012 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- 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 single crystal turbine rotor blade during a single heating schedule requiring only one furnace operation. The composition of the abrasive blade tip cap advantageously utilizes the high temperature performance capabilities of the single crystal alloy without significantly affecting its mechanical properties as a consequence of the processing necessary to permanently bond the abrasive blade tip cap to the rotor blade. A semi-rigid blade tip cap preform is first formed 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 and consolidate the preform. The rotor blade is then rapidly cooled in the vacuum furnace to retain the single crystal structure of the rotor blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.