公开(公告)号：US11635023B1

公开(公告)日：2023-04-25

申请号：US17715156

申请日：2022-04-07

Applicant: Hamilton Sundstrand Corporation

Inventor： Stephen H. Taylor ,  Malcolm P. MacDonald

IPC: F02C6/18 ,  F02C7/224 ,  F01D15/10

Abstract: A CO2 bottoming cycle system includes a first compressor operatively connected to a first turbine through a first shaft. A first generator is operatively connected to the first shaft. A second compressor is fluidically connected to the first compressor. The second compressor is operatively connected to a second turbine through a second shaft. A second generator is operatively connected to the second shaft. The first turbine is fluidically connected to the second turbine.

公开(公告)号：US20240266566A1

公开(公告)日：2024-08-08

申请号：US18163814

申请日：2023-02-02

Applicant: Hamilton Sundstrand Corporation

Inventor： Malcolm P. MacDonald ,  Ram Ranjan

IPC: H01M8/04701 ,  B60L50/70 ,  B60L58/33 ,  B64D13/06 ,  B64D27/24 ,  B64D33/08 ,  H01M8/04014 ,  H01M8/04111

CPC classification number: H01M8/04701 ,  B60L50/70 ,  B60L58/33 ,  B64D13/06 ,  B64D27/24 ,  B64D33/08 ,  H01M8/04014 ,  H01M8/04111 ,  B60L2200/10 ,  B64D2013/0618 ,  B64D2013/0648 ,  H01M2250/20

Abstract: In accordance with at least one aspect of this disclosure, an emergency power unit system for an aircraft includes a fuel cell system configured to generate power using a fuel and an oxidant, and an oxidant supply system fluidly connected to the fuel cell system to supply the oxidant to the fuel cell system via an oxidant supply line. The oxidant supply system is fluidly connected to an environmental control system of an aircraft.

公开(公告)号：US20240258534A1

公开(公告)日：2024-08-01

申请号：US18102488

申请日：2023-01-27

Applicant: Hamilton Sundstrand Corporation

Inventor： Malcolm P. MacDonald

IPC: H01M8/04029 ,  B60L50/70 ,  B60L58/32 ,  B64D27/24 ,  B64D33/08 ,  H01M8/04007

CPC classification number: H01M8/04029 ,  B60L50/70 ,  B60L58/32 ,  B64D27/24 ,  B64D33/08 ,  H01M8/04059 ,  H01M8/04067 ,  B60L2200/10 ,  H01M2250/20

Abstract: In accordance with at least one aspect of this disclosure, an emergency power unit for an aircraft includes, a fuel cell system configured to generate power using a fuel and an oxidant. A thermal management system is in thermal communication with the fuel cell system to divert heat from the fuel cell system to the thermal management system.

公开(公告)号：US20240258540A1

公开(公告)日：2024-08-01

申请号：US18161728

申请日：2023-01-30

Applicant: Hamilton Sundstrand Corporation

Inventor： Malcolm P. MacDonald

IPC: H01M8/04225 ,  B60L50/60 ,  B60L50/70 ,  B60L58/33 ,  B64D27/24 ,  H01M8/04007 ,  H01M8/04111 ,  H01M16/00

CPC classification number: H01M8/04225 ,  B60L50/60 ,  B60L50/70 ,  B60L58/33 ,  B64D27/24 ,  H01M8/04067 ,  H01M8/04111 ,  H01M16/006 ,  B60L2200/10 ,  B64D2221/00 ,  H01M2250/20

Abstract: In accordance with at least one aspect of this disclosure, an emergency power unit system for an aircraft includes, a fuel cell system configured to generate power using a fuel and an oxidizer and to supply electrical power to an aircraft electrical bus in at least a fuel cell operational mode. An electrical storage is operatively connected to the aircraft electrical bus and directly connected to the fuel cell system to provide electrical power to the aircraft electrical bus and to the fuel cell system in a fuel cell start up mode.