公开(公告)号：US20250058891A1

公开(公告)日：2025-02-20

申请号：US18610868

申请日：2024-03-20

Applicant: The Boeing Company

Inventor： Chellappa Balan ,  Michael F. Stoia ,  Charles Aguilar ,  Drew Christopher Hoffman

IPC: B64D37/34 ,  B64D13/06 ,  B64D13/08 ,  B64D33/10 ,  B64D37/04 ,  B64D37/30 ,  B64D41/00 ,  F02C7/22 ,  H01M8/04029

Abstract: An aircraft thermal management system comprising a high temperature loop and a low temperature loop. The high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. The low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.

公开(公告)号：US11430998B2

公开(公告)日：2022-08-30

申请号：US16735464

申请日：2020-01-06

Applicant: The Boeing Company

Inventor： Marianne E. Mata ,  Ali Yousefiani ,  Adam J. Lang ,  Bruno Zamorano Senderos ,  Chellappa Balan

IPC: H01M8/0202 ,  H01M8/2404 ,  H01M8/0271 ,  H01M8/12

Abstract: A fuel cell stack is described. The fuel cell stack comprises an interconnect assembly comprising a cathode-side interface coupled to an interconnect via a first joint, and an anode-side interface coupled to the interconnect via a second joint, the interconnect assembly having a first coefficient of thermal expansion (CTE) at an interface side of the interconnect assembly. The fuel cell stack further comprises a fuel cell element coupled to the interconnect assembly at the interface side via a hermetic seal, the fuel cell element having a second CTE at the interface side, the first CTE and the second CTE satisfying a predetermined CTE matching condition.

公开(公告)号：US20250058889A1

公开(公告)日：2025-02-20

申请号：US18610526

申请日：2024-03-20

Applicant: The Boeing Company

Inventor： Chellappa Balan ,  Michael F. Stoia ,  Charles Aguilar ,  Drew Christopher Hoffman ,  Luis Gonzalez ,  Daniel A. Watts

IPC: B64D37/04 ,  B64D27/31 ,  B64D27/355 ,  B64D33/08 ,  B64D37/20 ,  B64D37/30 ,  F17C9/00 ,  H01M8/04007 ,  H01M8/04082

Abstract: An aircraft comprises a fuselage, wings connected to the fuselage, engines connected to the wings, and liquid hydrogen tanks. Each engine in the engines comprises a nacelle, an electric motor within the nacelle, a fuel cell stack within the nacelle, and a nacelle heat exchanger within the nacelle that receives air flowing through an inlet in the nacelle. The liquid hydrogen tanks are configured to store liquid hydrogen, wherein the liquid hydrogen tanks extend along an outside of the fuselage and above the wings and below windows in the fuselage.

公开(公告)号：US20210210768A1

公开(公告)日：2021-07-08

申请号：US16735464

申请日：2020-01-06

Applicant: The Boeing Company

Inventor： Marianne E. Mata ,  Ali Yousefiani ,  Adam J. Lang ,  Bruno Zamorano Senderos ,  Chellappa Balan

IPC: H01M8/0202 ,  H01M8/0271 ,  H01M8/2404

Abstract: A fuel cell stack is described. The fuel cell stack comprises an interconnect assembly comprising a cathode-side interface coupled to an interconnect via a first joint, and an anode-side interface coupled to the interconnect via a second joint, the interconnect assembly having a first coefficient of thermal expansion (CTE) at an interface side of the interconnect assembly. The fuel cell stack further comprises a fuel cell element coupled to the interconnect assembly at the interface side via a hermetic seal, the fuel cell element having a second CTE at the interface side, the first CTE and the second CTE satisfying a predetermined CTE matching condition.

公开(公告)号：US20250059933A1

公开(公告)日：2025-02-20

申请号：US18610580

申请日：2024-03-20

Applicant: The Boeing Company

Inventor： Chellappa Balan ,  Michael F. Stoia ,  Charles Aguilar ,  Drew Christopher Hoffman

IPC: B64C3/36 ,  F02K3/06

Abstract: A heat exchanger system for an aircraft comprises nacelle having an inlet and an outlet, a nacelle heat exchanger within the nacelle, and a fan system within the nacelle. Air flows into the nacelle through the inlet and out of the nacelle through the outlet. The nacelle heat exchanger is configured to transfer heat away from a coolant using the air in an airflow to the nacelle heat exchanger. The fan system is configured to increase the airflow to the nacelle heat exchanger.

公开(公告)号：US20250058885A1

公开(公告)日：2025-02-20

申请号：US18610816

申请日：2024-03-20

Applicant: The Boeing Company

Inventor： Chellappa Balan

IPC: B64D13/08 ,  B64D27/355 ,  H01M8/04014

Abstract: An aircraft air management system comprises an air heat exchanger; an intercooler; and a conduit system connected to the air heat exchanger, the intercooler, and a fuel cell stack. Heated air flows through the conduit system to the air heat exchanger. The air heat exchanger is configured to cool the heated air to form cooler air, wherein the cooler air flows from the air heat exchanger through the conduit system to the intercooler; and the intercooler is configured to cool the cooler air to form cooled air, wherein the cooled air flows from the intercooler through the conduit system to the fuel cell stack.

公开(公告)号：US20250058884A1

公开(公告)日：2025-02-20

申请号：US18610742

申请日：2024-03-20

Applicant: The Boeing Company

Inventor： Chellappa Balan ,  Charles Aguilar

IPC: B64D13/08 ,  B60L50/72 ,  B60L58/33 ,  B64D13/00 ,  H01M8/04007 ,  H01M8/04029

Abstract: Aircraft comprises a heater system, a conduit system thermally connected to fuel cell stacks, a pump system, and a controller. The heater system is configured to heat a coolant. The coolant flows through the conduit system. The pump system is configured to circulate the coolant through the conduit system to the fuel cell stacks. The controller is configured to control the heater system to heat the coolant to form a heated coolant. The controller is configured to control the pump system to circulate the heated coolant through the conduit system. The controller is configured to control the conduit system to circulate the heated coolant to a subset of the fuel cell stacks, wherein the heated coolant causes the subset of the fuel cell stacks to reach an operating temperature.

公开(公告)号：US20200212461A1

公开(公告)日：2020-07-02

申请号：US16237787

申请日：2019-01-02

Applicant: The Boeing Company

Inventor： Marianne E. Mata ,  Chellappa Balan ,  Tina Stoia ,  Shailesh Atreya

IPC: H01M8/04089 ,  H01M8/2425 ,  H01M8/249 ,  H01M8/0612

Abstract: In an example, a system for increasing solid oxide fuel cell (SOFC) efficiency is described. The system comprises a series of SOFC stacks, a fuel flow path through the series, and an air flow path through the series. In the fuel flow path between two sequential SOFC stacks in the series, fuel exhaust from a first SOFC stack of the two sequential SOFC stacks is input into a second SOFC stack of the two sequential SOFC stacks. In the air flow path between the two sequential SOFC stacks, air exhaust from the first SOFC stack is input into the second SOFC stack. Further, between the two sequential SOFC stacks, (i) the fuel flow path comprises a fuel inlet positioned for injecting fuel into the fuel flow path and/or (ii) the air flow path comprises an air inlet positioned for injecting air into the air flow path.

公开(公告)号：US10069150B2

公开(公告)日：2018-09-04

申请号：US14697368

申请日：2015-04-27

Applicant: The Boeing Company

Inventor： Marianne E. Mata ,  Tina R. Stoia ,  Chellappa Balan

IPC: H01M8/04 ,  H01M8/04014 ,  H01M8/04007 ,  H01M8/04111 ,  H01M8/04701 ,  H01M8/124

Abstract: Systems and methods provide for the thermal management of a high temperature fuel cell. According to embodiments described herein, a non-reactant coolant is routed into a fuel cell from a compressor or a ram air source. The non-reactant coolant absorbs waste heat from the electrochemical reaction within the fuel cell. The heated coolant is discharged from the fuel cell and is vented to the surrounding environment or directed through a turbine. The energy recouped from the heated coolant by the turbine may be used to drive the compressor or a generator to create additional electricity and increase the efficiency of the fuel cell system. A portion of the heated coolant may be recycled into the non-reactant coolant entering the fuel cell to prevent thermal shock of the fuel cell.

公开(公告)号：US20180114995A1

公开(公告)日：2018-04-26

申请号：US15332191

申请日：2016-10-24

Applicant: The Boeing Company

Inventor： Tina Stoia ,  Shailesh Atreya ,  Chellappa Balan ,  David Whelan ,  David J. GIll ,  Vincent J. Castelli

IPC: H01M8/04014 ,  H01M8/04225 ,  H01M8/04111 ,  H01M8/0612

CPC classification number: H01M8/04022 ,  H01M8/04111 ,  H01M8/04225 ,  H01M8/0618 ,  H01M8/0662 ,  H01M2008/1293 ,  H01M2250/20 ,  H01M2250/402 ,  Y02B90/12 ,  Y02E60/525 ,  Y02T90/32

Abstract: A rapid start power unit and a method of operating a rapid start power unit are disclosed. A fuel cell converts combustible fuel into electrical power during a normal operational period after an initial start-up period when little to no electrical energy is produced. One combustion chamber receives unspent fuel emitted by the fuel cell and combusts the unspent fuel to generate a first heated gas stream. Another combustion chamber receives combustible fuel and burns the combustible fuel to generate a second heated gas stream during the initial start-up period. A turbine receives and is driven by the first and second heated gas streams to drive a drive shaft. A generator coupled to the drive shaft generates electrical power during the initial start-up period and supplemental power during the normal operational period. In an alternative embodiment, a two-stage combustion chamber is used instead of two serially-arranged separate combustion chambers.