Patent ID: 6763654
Filing Date: 2004-07-20
Classification: F01D,F02C,F02K,Y02T

Abstract:
A gas turbine engine turbine assembly comprising:a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft and rotatable about an engine centerline, a low pressure turbine having a low pressure turbine flowpath and located aft of said high pressure spool, said low pressure turbine having counter rotatable low pressure inner and outer shaft turbines, said low pressure turbine having low pressure inner and outer shafts respectively which are at least in part rotatably disposed coaxial with and radially inwardly of said high pressure spool, said low pressure inner shaft turbine including first low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a forward fan blade row by said low pressure inner shaft, said low pressure outer shaft turbine including second low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a aft fan blade row by said low pressure outer shaft, a single direction of rotation booster having at least a rotatable first row of booster blades drivenly connected to said low pressure outer shaft and axially located aft and downstream of said aft fan blade row, and at least one row of low pressure variable vanes disposed across said low pressure turbine flowpath between said low pressure inner and outer shaft turbines.