Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
US11181120B2 · kind B2 · utility
1Cited by
7References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 21, 2018 |
| Grant date | Nov 23, 2021 |
| Priority date | — |
| Expiry date | Jun 1, 2039 |
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 compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.