Gas turbine engine with low pressure turbine comprising counter rotatable low pressure inner and outer shaft turbines

摘要

An aircraft gas turbine engine (10) includes a low pressure turbine (26) having a low pressure turbine flowpath (28) and low pressure inner and outer shaft turbines (41 and 42) with counter rotatable low pressure inner and outer shaft turbine rotors (200 and 202), respectively. The low pressure inner and outer shaft turbine rotors (200 and 202) include low pressure first and second turbine blade rows (138 and 148) disposed across the turbine flowpath which are drivingly connected to first and second fan blade rows (13 and 15) by low pressure inner and outer shafts (130 and 140), respectively. At least one row of low pressure variable vanes (210) is operably disposed across the low pressure turbine flowpath between the low pressure inner and outer shaft turbines (41 and 42). The low pressure first turbine blade rows (138) of the low pressure inner shaft turbine (41) may be in tandem with or interdigitated with the second turbine blade rows (148) of the low pressure outer shaft turbines (42).