Local pressure side blade tip lean
US10947851B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 19, 2018 |
| Grant date | Mar 16, 2021 |
| Priority date | — |
| Expiry date | Apr 23, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade of a gas turbine engine includes a pressure side, and a suction side opposite the pressure side and defining a rotor blade profile therebetween, the pressure side and the suction side each extending from a blade root to a blade tip. The rotor blade defines a cross-sectional median line midway between the pressure side and the suction side. The cross-sectional median line extends in a generally radial direction from the blade root to a lean point between the blade root and the blade tip. The cross-sectional median line extends off of radial from the lean point to the blade tip, defining a lean of the rotor blade between the lean point and the blade tip.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.