Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US9976433B2 · kind B2 · utility
3Cited by
60References
23Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 2, 2010 |
| Grant date | May 22, 2018 |
| Priority date | — |
| Expiry date | Jun 1, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.