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    Engine core assistance
    4.
    发明授权
    Engine core assistance 有权

    公开(公告)号：US10934935B2

    公开(公告)日：2021-03-02

    申请号：US15419040

    申请日：2017-01-30

    申请人： GE Aviation Systems LLC

    发明人： Manish Ashvinkumar Dalal ,  Paul Robert Gemin

    IPC分类号： F02C7/32 ,  F02C6/14 ,  F02C6/20 ,  F02C7/36 ,  F02C6/00 ,  F02C9/16 ,  F01D15/10 ,  H02P101/30

    摘要： One example aspect of the present disclosure is directed to a method for operating a gas turbine engine. One example aspect of the present disclosure is directed to a method for operating a gas turbine engine, the gas turbine engine including at least a high pressure spool and a low pressure spool. The method includes causing, by one or more control devices, electrical power to be drawn from the high pressure spool and the low pressure spool into a power distribution system. The method includes determining, by the one or more control devices, a power adjustment event associated with the high pressure spool. The method includes initiating, by the one or more control devices, a power assist operation to redirect electrical power to the high pressure spool based at least in part on the power adjustment event.

    SYSTEMS AND METHODS OF POWER ALLOCATION FOR HYBRID ELECTRIC ARCHITECTURE
    5.
    发明申请
    SYSTEMS AND METHODS OF POWER ALLOCATION FOR HYBRID ELECTRIC ARCHITECTURE 审中-公开

    公开(公告)号：US20180291807A1

    公开(公告)日：2018-10-11

    申请号：US15479495

    申请日：2017-04-05

    申请人： GE Aviation Systems LLC

    发明人： Manish Ashvinkumar Dalal

    IPC分类号： F02C6/20 ,  B64D27/02 ,  B64D41/00 ,  F01D15/10 ,  F02C6/14 ,  F02C7/32 ,  H02J7/34 ,  B60L11/18 ,  F02N11/08

    摘要： Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.

    Systems and methods of power allocation for turboprop and turboshaft aircraft
    6.
    发明授权
    Systems and methods of power allocation for turboprop and turboshaft aircraft 有权

    公开(公告)号：US11448135B2

    公开(公告)日：2022-09-20

    申请号：US16937147

    申请日：2020-07-23

    申请人： GE AVIATION SYSTEMS LLC

    发明人： Manish Ashvinkumar Dalal

    IPC分类号： F02C7/32 ,  F01D15/10 ,  B64D27/24 ,  F02C7/36 ,  B64D41/00

    摘要： Systems and method for an electrical system on an aircraft are provided. In example aspects, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to multiple high power demand loads. A propulsion system and a multiple aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the propulsion system, and the secondary aircraft systems bus.

    AIRCRAFT STARTING AND GENERATING SYSTEM
    7.
    发明申请
    AIRCRAFT STARTING AND GENERATING SYSTEM 有权

    公开(公告)号：US20210384853A1

    公开(公告)日：2021-12-09

    申请号：US16893879

    申请日：2020-06-05

    申请人： GE Aviation Systems LLC

    发明人： Hao Huang ,  Xiaochuan Jia ,  Manish Ashvinkumar Dalal

    IPC分类号： H02P9/08 ,  H02M7/5387 ,  F02C7/268 ,  F02N11/04 ,  F02N11/08

    摘要： An aircraft starting and generating system includes a starter/generator and an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. A four leg inverter is coupled with the DC power output and has an inverter/converter/controller (ICC) with a four leg MOSFET-based bridge configuration that drives the starter/generator in a start mode for starting a prime mover of the aircraft, and converts DC power to AC power in a generate mode of the starter/generator. A four leg bridge gate driver is configured to drive the four leg MOSFET-based bridge using pulse width modulation (PWM) during start and generate mode.

    SYSTEMS AND METHODS OF POWER ALLOCATION FOR TURBOPROP AND TURBOSHAFT AIRCRAFTS
    10.
    发明申请
    SYSTEMS AND METHODS OF POWER ALLOCATION FOR TURBOPROP AND TURBOSHAFT AIRCRAFTS 有权

    公开(公告)号：US20220025820A1

    公开(公告)日：2022-01-27

    申请号：US16937147

    申请日：2020-07-23

    申请人： GE AVIATION SYSTEMS LLC

    发明人： Manish Ashvinkumar Dalal

    IPC分类号： F02C7/32 ,  F01D15/10 ,  B64D27/24 ,  F02C7/36

    摘要： Systems and method for an electrical system on an aircraft are provided. In example aspects, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to multiple high power demand loads. A propulsion system and a multiple aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the propulsion system, and the secondary aircraft systems bus.