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FR3158705B1 - Electrical power generation system for a hybrid power source aircraft - Google Patents

Electrical power generation system for a hybrid power source aircraft

Info

Publication number
FR3158705B1
FR3158705B1 FR2400963A FR2400963A FR3158705B1 FR 3158705 B1 FR3158705 B1 FR 3158705B1 FR 2400963 A FR2400963 A FR 2400963A FR 2400963 A FR2400963 A FR 2400963A FR 3158705 B1 FR3158705 B1 FR 3158705B1
Authority
FR
France
Prior art keywords
gas
circuit
end portion
gas inlet
engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2400963A
Other languages
French (fr)
Other versions
FR3158705A1 (en
Inventor
Jean-Baptiste Desforges
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ascendance Flight Tech
Original Assignee
Ascendance Flight Tech
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ascendance Flight Tech filed Critical Ascendance Flight Tech
Priority to FR2400963A priority Critical patent/FR3158705B1/en
Priority to PCT/EP2025/052445 priority patent/WO2025163097A1/en
Publication of FR3158705A1 publication Critical patent/FR3158705A1/en
Application granted granted Critical
Publication of FR3158705B1 publication Critical patent/FR3158705B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/30—Aircraft characterised by electric power plants
    • B64D27/33—Hybrid electric aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Hybrid Electric Vehicles (AREA)

Abstract

Un système de génération de puissance électrique pour un aéronef à source d’énergie hybride comprend un moteur (23) à combustion agencé pour fournir une puissance mécanique. Le système comprend en outre une électronique de puissance (21) agencée pour convertir la puissance mécanique fournie par le moteur (23) en puissance électrique pour la propulsion de l’aéronef. Le système comprend en outre un échangeur thermique (33) relié à l’électronique de puissance (21). Le système comprend en outre une entrée de gaz (11) et une sortie de gaz (13). Le système comprend encore un circuit gazeux reliant fluidiquement l’entrée de gaz (11) à la sortie de gaz (13). Le circuit gazeux débouche sur la sortie de gaz (13) au moins par une conduite d’évacuation (41). Cette conduite d’évacuation (41) présente une portion d’extrémité (42), à l’opposé de la sortie de gaz (13). Le circuit gazeux comprend un premier circuit, agencé pour alimenter le moteur (23) en air provenant de l’entrée de gaz (11) et pour évacuer des gaz d’échappement du moteur (23) vers la portion d’extrémité (42) de la conduite d’évacuation (41). Le circuit gazeux comprend en outre un deuxième circuit, reliant fluidiquement l’entrée de gaz (11) à la portion d’extrémité (42) de la conduite d’évacuation (41). Le deuxième circuit est agencé pour recevoir une circulation d’air provenant de l’entrée de gaz (11) et propre à refroidir l’échangeur thermique (33). Cette circulation d’air est générée par effet de pompe à jet lorsque les gaz d’échappement traversent la portion d’extrémité (42) de la conduite d’évacuation (41). Figure d’abrégé : [Fig.1]An electrical power generation system for a hybrid-powered aircraft includes a combustion engine (23) arranged to provide mechanical power. The system further includes power electronics (21) arranged to convert the mechanical power supplied by the engine (23) into electrical power for aircraft propulsion. The system further includes a heat exchanger (33) connected to the power electronics (21). The system further includes a gas inlet (11) and a gas outlet (13). The system also includes a gas circuit fluidly connecting the gas inlet (11) to the gas outlet (13). The gas circuit terminates at least at the gas outlet (13) via a discharge line (41). This discharge line (41) has an end portion (42) opposite the gas outlet (13). The gas circuit comprises a first circuit, arranged to supply the engine (23) with air from the gas inlet (11) and to discharge exhaust gases from the engine (23) to the end portion (42) of the discharge pipe (41). The gas circuit further comprises a second circuit, fluidly connecting the gas inlet (11) to the end portion (42) of the discharge pipe (41). The second circuit is arranged to receive an airflow from the gas inlet (11) to cool the heat exchanger (33). This airflow is generated by a jet pump effect as the exhaust gases pass through the end portion (42) of the discharge pipe (41). [Fig. 1]

FR2400963A 2024-01-31 2024-01-31 Electrical power generation system for a hybrid power source aircraft Active FR3158705B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2400963A FR3158705B1 (en) 2024-01-31 2024-01-31 Electrical power generation system for a hybrid power source aircraft
PCT/EP2025/052445 WO2025163097A1 (en) 2024-01-31 2025-01-30 System for generating electrical power for an aircraft with a hybrid energy source

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2400963A FR3158705B1 (en) 2024-01-31 2024-01-31 Electrical power generation system for a hybrid power source aircraft
FR2400963 2024-01-31

Publications (2)

Publication Number Publication Date
FR3158705A1 FR3158705A1 (en) 2025-08-01
FR3158705B1 true FR3158705B1 (en) 2026-01-02

Family

ID=90718466

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2400963A Active FR3158705B1 (en) 2024-01-31 2024-01-31 Electrical power generation system for a hybrid power source aircraft

Country Status (2)

Country Link
FR (1) FR3158705B1 (en)
WO (1) WO2025163097A1 (en)

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6651929B2 (en) * 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
JP2024507366A (en) * 2021-02-21 2024-02-19 ヴェルデゴ エアロ，インコーポレイテッド Aircraft Range Extended Energy Pod (REEP)

Also Published As

Publication number Publication date
WO2025163097A1 (en) 2025-08-07
FR3158705A1 (en) 2025-08-01

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Legal Events

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Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20250801

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