US 12,291,346 B2
Propulsion system for an aircraft and method for protecting the propulsion system
Darren Paget, Toulouse (FR); Vincent Lamonzie, Toulouse (FR); and Norberto Simionato Neto, Taufkirchen (DE)
Assigned to Airbus SAS, Blagnac (FR); and Airbus Operations SAS, Toulouse (FR)
Filed by Airbus SAS, Blagnac (FR); and Airbus Operations SAS, Toulouse (FR)
Filed on Mar. 13, 2023, as Appl. No. 18/182,899.
Claims priority of application No. 2202410 (FR), filed on Mar. 18, 2022.
Prior Publication US 2023/0294836 A1, Sep. 21, 2023
Int. Cl. B64D 33/10 (2006.01); B64D 27/24 (2006.01)
CPC B64D 33/10 (2013.01) [B64D 27/24 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A propulsion system for an aircraft, the propulsion system comprising:
at least two fuel cells,
an electric propulsion motor electrically connected to the at least two fuel cells,
at least two functional elements (EF),
at least two heat exchangers configured to permit heat exchange with ram air (RA), and
a cooling circuit configured to cool the at least two fuel cells and the at least two functional elements, such that, in operation, a heat-transfer fluid circulates in the cooling circuit in a predefined direction of flow, the cooling circuit being a closed circuit having at least one main segment, the flow of the heat-transfer fluid circulating entirely in the at least one main segment,
wherein the cooling circuit further comprises:
a primary circuit having:
at least one first main segment,
at least one first secondary segment that corresponds to each fuel cell and configured to cool each said fuel cell, and
at least one tertiary segment that corresponds to each heat exchanger for exchanging heat with ram air (RA),
a secondary circuit having:
at least one second main segment,
at least one second secondary segment that corresponds to each functional element and configured so as to cool each said functional element,
a pump located on the at least one second main segment, and
a reservoir containing heat-transfer fluid, and
a control unit comprising electronic circuitry,
wherein each first secondary segment and each tertiary segment has:
a leak detection device,
a shut-off valve, the shut-off valve at an inlet of the first secondary or tertiary segment relative to the predefined direction of flow, and
a non-return valve configured to prevent reflux of the heat-transfer fluid through the first secondary or tertiary segment in an opposite direction to the predefined direction of flow, the non-return valve at an outlet of the first secondary or tertiary segment, relative to the predefined direction of flow, and
wherein the control unit is configured to trigger a closure of the shut-off valve of a first secondary segment or a tertiary segment when a leak is detected by the leak detection device of said first secondary segment or said tertiary segment, so as to stop the circulation of the heat-transfer fluid through said first secondary segment or said tertiary segment, in order to maintain the operation of the at least two fuel cells or of the at least two functional elements that are cooled by the cooling circuit and are situated on other segments of the cooling circuit than said first secondary segment or said tertiary segment on which the leak has been detected.