Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines

摘要

A low pressure turbine section for an aircraft gas turbine engine includes a low pressure turbine flowpath and counter rotatable low pressure inner and outer shaft rotors having inner and outer shafts, respectively. The low pressure inner and outer shaft rotors include low pressure first and second turbine blade rows disposed across the turbine flowpath and drivingly connected to first and second fan blade rows, respectively. The first low pressure turbine blade rows are disposed downstream of the second low pressure turbine blade rows along said low pressure turbine flowpath. Rows of non-rotatable low pressure vanes are disposed across the low pressure turbine flowpath between the first low pressure turbine blade rows and between the second low pressure turbine blade rows. An annular vaneless gap may be located between an aftmost row of the second low pressure turbine blade rows and a forwardmost row of the first low pressure turbine blade rows.