초록 ▼

A method is provided for controlling a torque output of an hydrostatic motor in fluid communication with a variable displacement pump. At least one of the motor and pump has variable displacement capabilities. The method includes monitoring at least one motor condition of the hydrostatic motor and d

A method is provided for controlling a torque output of an hydrostatic motor in fluid communication with a variable displacement pump. At least one of the motor and pump has variable displacement capabilities. The method includes monitoring at least one motor condition of the hydrostatic motor and determining a displacement signal corresponding to the monitored motor condition. The variable displacement capabilities are controlled based on the displacement signal to reduce a torque ripple in the torque output of the hydrostatic motor.

대표청구항 ▼

A method is provided for controlling a torque output of an hydrostatic motor in fluid communication with a variable displacement pump. At least one of the motor and pump has variable displacement capabilities. The method includes monitoring at least one motor condition of the hydrostatic motor and d

A method is provided for controlling a torque output of an hydrostatic motor in fluid communication with a variable displacement pump. At least one of the motor and pump has variable displacement capabilities. The method includes monitoring at least one motor condition of the hydrostatic motor and determining a displacement signal corresponding to the monitored motor condition. The variable displacement capabilities are controlled based on the displacement signal to reduce a torque ripple in the torque output of the hydrostatic motor. otatable low pressure inner and outer shaft rotors including a rotatable drum extension from which blades of one of said first and second interdigitated turbine blade rows of said first and second low pressure turbine blade rows depend radially inwardly. 10. An assembly as claimed in claim 9 further comprising a forwardmost row of said low pressure second turbine blade rows interdigitated with an aftmost pair of said first low pressure turbine blade rows. 11. An assembly as claimed in claim 10 further comprising an odd number of one of said first low pressure turbine blade rows and said low pressure second turbine blade rows and an even number of another of said first low pressure turbine blade rows and said low pressure second turbine blade rows. 12. An assembly as claimed in claim 10 further comprising an odd number of said first low pressure turbine blade rows and an even number of said low pressure second turbine blade rows. 13. An assembly as claimed in claim 12 further comprising three of said first low pressure turbine blade rows and four of said low pressure second turbine blade rows. 14. An assembly as claimed in claim 2 further comprising: said low pressure inner shaft rotor including a rotating frame, said rotating frame including one of said low pressure first turbine blade rows, a portion of said low pressure first turbine blade rows depending radially inwardly from a radially outer second turbine drum supported by said rotating frame, an aftmost row of said low pressure first turbine blade rows mounted on a last stage turbine disk connected to said rotating frame, and said row of non-rotatable low pressure vanes disposed between said one of said low pressure first turbine blade rows of said rotating frame and said aftmost row of said low pressure first turbine blade rows. 15. An assembly as claimed in claim 2 further comprising: two forwardmost rows of said low pressure second turbine blade rows interdigitated with three aftmost rows of said first low pressure turbine blade rows, a rotatable drum on one of said counter rotatable low pressure inner and outer shaft rotors, said low pressure second turbine blade rows depending radially inwardly from said rotatable drum and interdigitated with said three aftmost rows of said first low pressure turbine blade rows and blades of one of said two forwardmost rows of said low pressure second turbine blade rows and said three aftmost rows of said first low pressure turbine blade rows depending radially inwardly from said rotatable drum. 16. An aircraft gas turbine engine assembly comprising: a high pressure rotor 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 rotor, said low pressure turbine including counter rotatable low pressure inner and outer shaft rotors having low pressure inner and outer shafts respectively which are at least in part rotatably disposed co-axial with and radially inwardly of said high pressure rotor, said low pressure inner shaft rotor including first low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a first fan blade row by said low pressure inner shaft, said low pressure outer shaft rotor including second low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a second fan blade row by said low pressure outer shaft, at least one booster drivingly connected to one of said low pressure inner and outer shafts and axially located between said first fan blade row and said high pressure rotor, said first and second fan blade rows disposed within a bypass duct radially outwardly bounded by a fan casing, said first low pressure turbine blade rows including at least one first interdigitated turbine blade row disposed b