Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
US11280199B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 21, 2018 |
| Grant date | Mar 22, 2022 |
| Priority date | — |
| Expiry date | Oct 5, 2040 |
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. 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 a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a ratio of a first arc distance along the mean camber line between the leading edge and a position of the local maximum thickness to a total arc distance along the mean camber line from the leading edge to the trailing edge. A value of the ratio increases from the root to a first position value, decreases from the first position value to a second position value and increases from the second position value to the tip. The first position value is at a spanwise location within 20% to 50% of the span.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.