Turbine section of high bypass turbofan
US10060357B2 · kind B2 · utility
20Cited by
95References
27Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 13, 2016 |
| Grant date | Aug 28, 2018 |
| Priority date | — |
| Expiry date | Oct 13, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.