TURBINE SECTION OF HIGH BYPASS TURBOFAN

摘要

A turbofan engine includes an engine case, a gaspath through the engine case, a fan having an array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A ratio of maximum gaspath radius along the low pressure turbine section to maximum radius of the fan blades is less than about 0.55. A bypass area ratio is greater than about 6.0. A ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than about 170 and a second turbine section.

主权项

1. A turbofan engine comprising:
an engine case; a gaspath through the engine case; a fan having an 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 fan drive turbine section having 3 to 6 blade stages; and a speed reduction mechanism coupling the fan drive turbine section to the fan, wherein: a ratio of maximum gaspath radius along the low pressure turbine section to maximum radius of the fan blades is less than about 0.55; a bypass area ratio is greater than about 6.0; a ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than about 170; and a second turbine section.