Turbine blade with tip vortex control and tip shelf
US10801325B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 27, 2017 |
| Grant date | Oct 13, 2020 |
| Priority date | — |
| Expiry date | Jul 9, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade for a gas turbine engine includes an airfoil which includes pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface. The airfoil extends from a 0% span position to a 100% span position at a tip. A mean chamber line is provided at the tip and extends from the leading edge to the trailing edge. The mean chamber line has a leading edge tangent line at the leading edge at the tip and a trailing edge tangent line at the trailing edge at the tip. The leading edge tangent line and the trailing edge tangent line intersect to provide a total camber angle in a range of −35° to 35°. The pressure side includes a tip shelf.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.