Abrasive material, especially for turbine blade tips
US4735656A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 29, 1986 |
| Grant date | Apr 5, 1988 |
| Priority date | — |
| Expiry date | Dec 29, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/20
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
An abrasive material comprised of a metal matrix and evenly distributed ceramic particulates, is made by mixing powder metal with the ceramic powder and heating to a temperature sufficient to melt most, but not all of the powder. In this way the ceramic does not float to the top of the material, yet a dense material is obtained. A nickel superalloy matrix will have at least some remnants of the original powder metal structure, typically some equiaxed grains, along with a fine dendritic structure, thereby imparting desirable high temperature strength when the abrasive material is applied to the tips of blades of gas turbine engines. Preferred matrices have a relatively wide liquidus-solidus temperature range, contain a melting point depressant, and a reactive metal to promote adhesion to the ceramic.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.