Gas turbine blade for an aircraft engine and method for coating a gas turbine blade
US9624781B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jan 10, 2013 |
| Grant date | Apr 18, 2017 |
| Priority date | — |
| Expiry date | Nov 21, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Embodiments relate to a gas turbine blade for an aircraft engine, the gas turbine blade having a flow leading edge, a flow trailing edge, a suction side, and a pressure side, where the suction side and pressure side extend from the flow leading edge to the flow trailing edge, wherein the gas turbine blade has a damping layer on the flow leading edge and the damping layer comprising at least one matrix material and particles held in position by this matrix material. Further embodiments relate to a method of coating a gas turbine blade and a gas turbine incorporating a plurality of gas turbine blades in accordance with embodiments of the invention.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.