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    Bowed rotor prevention system for turbomachinery
    6.
    发明授权
    Bowed rotor prevention system for turbomachinery 有权

    公开(公告)号：US11015659B2

    公开(公告)日：2021-05-25

    申请号：US16355297

    申请日：2019-03-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Vineet Sethi ,  Randall Kleen

    IPC: F16D23/02 ,  F01D25/20 ,  F01D15/08 ,  F01D15/10 ,  F01D15/12 ,  F16D41/00 ,  F01M1/02 ,  F01D19/00 ,  F01D25/34

    Abstract: A bowed-rotor prevention system for a turbomachine is disclosed. The system comprises a first turbomachine having a first shaft rotatably supported by a plurality of bearings, a second turbomachine having a second shaft rotatably coupled to the first rotatable shaft, and a pump having a third shaft rotatably coupled to the second shaft. The system further includes a gear box having a fourth shaft rotatably coupled to the third shaft by an clutch configured to operate in a freewheel condition when the first shaft is rotating faster than a first predetermined speed, and further configured to rotatably engage the fourth shaft to the third shaft when the first shaft is rotating slower than a second predetermined speed to thereby drive a rotation of the third shaft, wherein the first predetermined speed is faster than the second predetermined speed.

    System for cooling turbine shaft coupling
    9.
    发明授权
    System for cooling turbine shaft coupling 有权

    公开(公告)号：US11578621B2

    公开(公告)日：2023-02-14

    申请号：US16843848

    申请日：2020-04-08

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Ravinder Yerram ,  Balakrishnan Ponnuraj ,  Vineet Sethi ,  Jose Emmanuel Guillen ,  Tho Vankhanh Nguyen ,  Douglas Alan Jones ,  Abhinash Reddy Konatham

    IPC: F01D25/30 ,  F01D9/06 ,  F02C7/12

    Abstract: One or more cooling systems for ventilating a turbine and rotary shaft of a gas turbine system is provided. The gas turbine system includes a gas turbine engine and a turbine exhaust collector in separate enclosures. A first cooling system includes an educator that sucks exhaust gas through a diffuser and directs it out of the turbine exhaust collector enclosure based on suction pressure created from the high velocity of exhaust gas. A second cooling system include struts that enable the exhaust gas to flow from the diffusers to a ventilation flow stack. A third cooling system includes exhaust gas sucked from an opening to a top duct based on suction pressure created from the rotation of the rotary shaft disposed about a coupling. A guideway associated with the third cooling system also directs the exhaust gas to flow to the top duct. These cooling systems are designed to increase the efficiency of ventilating the turbine and rotary shaft, prevent misalignments of the rotary shaft, which may result in thermal stresses, and allow the use of the gas turbine systems in higher ambient temperature environments.

    SYSTEM FOR COOLING TURBINE SHAFT COUPLING
    10.
    发明申请
    SYSTEM FOR COOLING TURBINE SHAFT COUPLING 有权

    公开(公告)号：US20210317784A1

    公开(公告)日：2021-10-14

    申请号：US16843848

    申请日：2020-04-08

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Ravinder Yerram ,  Balakrishnan Ponnuraj ,  Vineet Sethi ,  Jose Emmanuel Guillen ,  Tho Vankhanh Nguyen ,  Douglas Alan Jones ,  Abhinash Reddy Konatham

    IPC: F02C7/18 ,  F01D25/12

    Abstract: One or more cooling systems for ventilating a turbine and rotary shaft of a gas turbine system is provided. The gas turbine system includes a gas turbine engine and a turbine exhaust collector in separate enclosures. A first cooling system includes an educator that sucks exhaust gas through a diffuser and directs it out of the turbine exhaust collector enclosure based on suction pressure created from the high velocity of exhaust gas. A second cooling system include struts that enable the exhaust gas to flow from the diffusers to a ventilation flow stack. A third cooling system includes exhaust gas sucked from an opening to a top duct based on suction pressure created from the rotation of the rotary shaft disposed about a coupling. A guideway associated with the third cooling system also directs the exhaust gas to flow to the top duct. These cooling systems are designed to increase the efficiency of ventilating the turbine and rotary shaft, prevent misalignments of the rotary shaft, which may result in thermal stresses, and allow the use of the gas turbine systems in higher ambient temperature environments.

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