Compressor rotor airfoil
US10760424B2 · kind B2 · utility
2Cited by
11References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 11, 2017 |
| Grant date | Sep 1, 2020 |
| Priority date | — |
| Expiry date | Feb 14, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.