Compressor rotor for supersonic flutter and/or resonant stress mitigation
US10670041B2 · kind B2 · utility
1Cited by
33References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 17, 2017 |
| Grant date | Jun 2, 2020 |
| Priority date | — |
| Expiry date | Apr 12, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.