Pressure ratio distributions for a gas turbine engine
US11149690B2 · kind B2 · utility
12Cited by
5References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 21, 2018 |
| Grant date | Oct 19, 2021 |
| Priority date | — |
| Expiry date | Jun 2, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine 10 is provided in a fan root to tip pressure ratio, defined as the ratio of the mean total pressure of the flow at the fan exit that subsequently flows through the engine core (P102) to the mean total pressure of the flow at the fan exit that subsequently flows through the bypass duct (P104), is no greater than a certain value. The gas turbine engine 10 may provide improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.