Repeating airfoil tip strong pressure profile
US11248622B2 · kind B2 · utility
0Cited by
14References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 2, 2016 |
| Grant date | Feb 15, 2022 |
| Priority date | — |
| Expiry date | Jun 13, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.