Tip vortex control
US8360731B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 4, 2009 |
| Grant date | Jan 29, 2013 |
| Priority date | — |
| Expiry date | Jun 14, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/70
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade for a gas turbine engine includes an attachment and an airfoil. The airfoil has a stagger angle, a base region, a transition region and a tip region. The stagger angle changes as the airfoil extends between the attachment and a tip. The base region is disposed adjacent to the attachment. The transition region is located between the base and the tip regions. A rate of the change of the stagger angle in the transition region is greater than a rate of the change of the stagger angle in the base region. The rate of the change of the stagger angle in the transition region is greater than a rate of change of the stagger angle in the tip region.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.