Turbine blade having a fused metal-ceramic tip
US4802828A · kind A · utility
56Cited by
6References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 29, 1986 |
| Grant date | Feb 7, 1989 |
| Priority date | — |
| Expiry date | Dec 29, 2006 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49337
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine blade has an abrasive material tip with a fused superalloy matrix and evenly distributed ceramic particulate. The matrix will have a desirable metallurgical structure characterized by fine dendrites and remanants of the original powder metal structure from which it was made. Due to the fusion of the tip, the peripheral edge will tend to be curved. To lessen the effect of thermal strains on such an abrasive tip, a sheath of a superalloy, such as a portion of the turbine blade substrate, extends along the side of the abrasive. The sheath may be present only in the thicker leading edge part of the blade airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.