Turbine compressor blade tip resistant to metal transfer
US9341066B2 · kind B2 · utility
8Cited by
4References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 18, 2012 |
| Grant date | May 17, 2016 |
| Priority date | — |
| Expiry date | Feb 28, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abradable.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.