Geared gas turbine engine
US11781491B2 · kind B2 · utility
0Cited by
5References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 15, 2022 |
| Grant date | Oct 10, 2023 |
| Priority date | — |
| Expiry date | Nov 15, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.