Compressor rotor for supersonic flutter and/or resonant stress mitigation
US11353038B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 29, 2020 |
| Grant date | Jun 7, 2022 |
| Priority date | — |
| Expiry date | Jul 17, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.