公开(公告)号：US10913543B2

公开(公告)日：2021-02-09

申请号：US15791475

申请日：2017-10-24

Applicant: GE Aviation Systems Limited

Inventor： Michael David Bailey ,  Colin John Halsey

IPC: H02J7/00 ,  H01M10/44 ,  H01M10/46 ,  B64D41/00 ,  H01M8/0612 ,  H01M8/0656 ,  H01M8/04082 ,  H01M8/04828 ,  H01M16/00 ,  H01M8/086 ,  H01M8/1018 ,  H01M8/124 ,  H01M8/083 ,  H01M8/14 ,  H01M8/18

Abstract: Systems and methods for providing power to one or more loads on an aircraft are provided. A power system for an aircraft can include a first fuel cell configured to provide base power to one or more loads on the aircraft. The power system can further include a second fuel cell configured to provide peak power to the one or more loads on the aircraft. The peak power can be a power exceeding the base power. The power system can further include an energy storage device configured to provide transient power to the one or more loads on the aircraft. The transient power can be a power exceeding the peak power. The power system can further include a controller configured to control delivery of power from the first fuel cell, the second fuel cell, and the energy storage device to the one or more loads on the aircraft.

公开(公告)号：US11040875B2

公开(公告)日：2021-06-22

申请号：US15778977

申请日：2015-11-24

Applicant: GE Aviation Systems Limited

Inventor： Colin John Halsey ,  Michael David Bailey ,  Ross Jonathan Williams

IPC: C01B3/06 ,  C01B3/00 ,  C01B3/04 ,  B01J7/02 ,  H01M8/0606

Abstract: A hydrogen storage system includes a pressure-sealed storage unit defining an interior and having an outlet, an upper manifold and a lower manifold separated by a dividing plane having a set of ports, a set of chambers, and a hydrogen storage, wherein at least some hydrogen gas is supplied to the outlet.

公开(公告)号：US10926870B2

公开(公告)日：2021-02-23

申请号：US15824528

申请日：2017-11-28

Applicant: GE Aviation Systems Limited

Inventor： Colin John Halsey ,  Michael David Bailey

IPC: B64D31/14 ,  B64C25/22 ,  B64C13/40 ,  H02J4/00 ,  B64D41/00 ,  H02J7/34 ,  F15B20/00

Abstract: A method and apparatus for operating a power system architecture including an electrical power storage system, a power distribution bus selectively connected with the electrical power storage device, a hydraulic pump selectively connected with the electrical power storage device and a controller module communicatively connected with the electrical power storage system and the hydraulic pump.

公开(公告)号：US10396565B2

公开(公告)日：2019-08-27

申请号：US15569797

申请日：2015-05-06

Applicant: GE Aviation Systems Limited

Inventor： Michael David Bailey ,  Colin John Halsey ,  Ross Jonathan Williams

IPC: H02J4/00 ,  H02J3/14 ,  H02J13/00 ,  B64D47/00 ,  H02J3/28 ,  H02J3/00 ,  B64D11/04 ,  B64D15/12

Abstract: A system for aircraft power distribution (100) includes a source of energy (112) to deliver an input power; a bus contactor (122); a set of switches (130) connected between the bus contactor and a set of essential and non-essential devices (132); a current analysis component (315) to determine a power level drawn from the source of current by the set of essential and non-essential devices (132); a variation reduction component (317) to determine an energization schedule of the set of essential and non-essential devices (132) based on reducing temporal variation in the input power drawn from the source of energy (112) to the bus contactor (122); and a switch control component (319) configured to adjust the set of switches (130) according to the energization schedule. If too much power is drawn, the set of switches (130) will be configured such as not to exceed the maximum power rating of the source (112).

公开(公告)号：US10814992B2

公开(公告)日：2020-10-27

申请号：US15814655

申请日：2017-11-16

Applicant: GE Aviation Systems Limited

Inventor： Colin John Halsey ,  Michael David Bailey

IPC: B64D27/24 ,  B64D41/00 ,  B64C13/36

Abstract: A power source for an aircraft including a solid oxide fuel cell and a proton exchange membrane fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell.

公开(公告)号：US20180155044A1

公开(公告)日：2018-06-07

申请号：US15824528

申请日：2017-11-28

Applicant: GE Aviation Systems Limited

Inventor： Colin John Halsey ,  Michael David Bailey

IPC: B64D31/14 ,  B64C13/40

CPC classification number: B64C25/22 ,  B64C13/40 ,  B64D41/00 ,  B64D2221/00 ,  F15B20/002 ,  F15B20/004 ,  F15B2211/20515 ,  F15B2211/20569 ,  F15B2211/625 ,  F15B2211/8752 ,  F15B2211/8757 ,  H02J4/00 ,  H02J7/34

Abstract: A method and apparatus for operating a power system architecture including an electrical power storage system, a power distribution bus selectively connected with the electrical power storage device, a hydraulic pump selectively connected with the electrical power storage device and a controller module communicatively connected with the electrical power storage system and the hydraulic pump.