Blade cutback distribution in rotor for noise reduction
US11041388B2 · kind B2 · utility
4Cited by
17References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 30, 2015 |
| Grant date | Jun 22, 2021 |
| Priority date | — |
| Expiry date | Dec 14, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes rotor having a hub, and a plurality of blades extending generally radially from the hub. Each of the blades has an airfoil portion. The airfoil portion has a leading edge and a trailing edge defining a chordwise direction, and a root and a tip defining a spanwise direction. Only a sub-set of the blades has a cutback at at least one of the trailing edge and the leading edge. A method of designing and a method of assembling a rotor having noise reduction properties in a gas turbine engine is also presented.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.