Direct drive electrically-geared turbofan
US-2024218837-A1 · Jul 4, 2024 · US
US9010085B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9010085-B2 |
| Application number | US-201213599175-A |
| Country | US |
| Kind code | B2 |
| Filing date | Aug 30, 2012 |
| Priority date | Aug 1, 2007 |
| Publication date | Apr 21, 2015 |
| Grant date | Apr 21, 2015 |
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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 ratio is below about 170.
Opening claim text (preview).
What is claimed is: 1. A turbofan engine comprising: an engine case; a gaspath through the engine case; a fan having a circumferential array of fan blades; a compressor in fluid communication with the fan; a combustor in fluid communication with the compressor; a turbine in fluid communication with the combustor, the turbine having a low pressure turbine section having 3 to 6 blade stages; and a speed reduction mechanism coupling the low pressure turbine section to the…
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