Method for distribution of cooling air for electrical equipment installed in an avionic bay and aircraft equipped with such a bay
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F28D-015/00
H05K-007/20
H05K-007/14
출원번호
US-0469575
(2012-05-11)
등록번호
US-9681585
(2017-06-13)
우선권정보
FR-11 01467 (2011-05-13)
발명자
/ 주소
Rebeyrotte, Vincent
Caron, Jean-Christophe
출원인 / 주소
AIRBUS OPERATIONS (SAS)
대리인 / 주소
Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
A method for distribution of cooling air for cooling an electrical equipment item installed in an avionic bay. Cooling air is drawn from an air vein, then passes into a first pressure zone in fluidic communication with the air vein and then into a second pressure zone in fluidic communication with b
A method for distribution of cooling air for cooling an electrical equipment item installed in an avionic bay. Cooling air is drawn from an air vein, then passes into a first pressure zone in fluidic communication with the air vein and then into a second pressure zone in fluidic communication with both the first pressure zone and the electrical equipment. The second pressure zone extends beneath a largest dimension (e.g., length) of electronic boards of the electrical equipment to be cooled.
대표청구항▼
1. A method for distribution of cooling air for heat-dissipating aircraft electrical equipment, the method using a cooling air vein configured to introduce air to cool the heat-dissipating aircraft electrical equipment, the heat-dissipating aircraft electrical equipment to be cooled being disposed a
1. A method for distribution of cooling air for heat-dissipating aircraft electrical equipment, the method using a cooling air vein configured to introduce air to cool the heat-dissipating aircraft electrical equipment, the heat-dissipating aircraft electrical equipment to be cooled being disposed above the cooling air vein, the method comprising: forming a first pressure zone in fluidic communication with the cooling air vein;forming a second pressure zone in fluidic communication with the first pressure zone, the second pressure zone having an extension dimension extending along an extension dimension greater than an extension dimension of the first pressure zone and being in fluidic communication with an interior of a compartment configured to house the heat-dissipating aircraft electrical equipment to be cooled;filtering at least one part of the cooling air by passage, along an axial direction, through a first separation grille between the cooling air vein and the first pressure zone;filtering said at least one part of the cooling air filtered beforehand by passage, along the axial direction, through a second separation grille between the first pressure zone and the second pressure zone; andfiltering said at least one part of the cooling air by passage through a third separation grille, said at least one part of the cooling air being filtered beforehand by passage through the second separation grille,wherein the first pressure zone is downstream of the cooling air vein, and the second pressure zone is downstream of the first pressure zone and the cooling air vein, andwherein the third separation grille is arranged upstream of and disposed below a portion of the interior of the compartment configured to house the heat-dissipating aircraft electrical equipment to be cooled. 2. The method according to claim 1, wherein the second pressure zone extends at a lower part of the heat-dissipating aircraft electrical equipment, beneath electronic boards of the heat-dissipating aircraft electrical equipment to be cooled, along the extension dimension, which corresponds at least to a largest dimension of the electronic boards. 3. The method according to claim 1 or 2, wherein the cooling air vein extends along a horizontal direction, cooling air being drawn from the cooling air vein along a vertical direction, and the second pressure zone extending horizontally. 4. The method according to claim 1, wherein said forming the first and second pressure zones is based on determining one or more of a pressure drop between the cooling air vein and the first pressure zone, determining a pressure drop between the first pressure zone and the second pressure zone, and determining a pressure drop between the second pressure zone and the interior of the heat-dissipating aircraft electrical equipment to be cooled, so as to set a distribution of the cooling air. 5. The method according to claim 1, wherein one or more of the second separation grille and the third separation grille includes apertures that are offset transversely in relation to respective apertures of one or more other separation grilles of the first separation grille, the second separation grille and the third separation grille, through which the cooling air passes along the axial direction. 6. An avionic bay comprising: electrical equipment to be cooled; anda cooling air vein, disposed underneath the electrical equipment, to provide cooling air;a first pressure zone in fluidic communication with the cooling air vein to receive the cooling air from the cooling air vein;a second pressure zone in fluidic communication with an interior of a compartment configured to house the electrical equipment;a first separation grille disposed between the cooling air vein and the first pressure zone;a second separation grille disposed between the first pressure zone and the second pressure zone; anda third separation grille disposed between the second pressure zone and a portion of the interior of the compartment configured to house the electrical equipment,wherein the second pressure zone is in fluidic communication with the first pressure zone so as to produce a distribution of cooling air in the portion of the interior of the compartment configured to house the electrical equipment, the second pressure zone extending along an extension dimension greater than an extension dimension of the first pressure zone,wherein the first pressure zone is downstream of the cooling air vein, and the second pressure zone is downstream of the first pressure zone and the cooling air vein, andwherein the third separation grille is arranged below the portion of the interior of the compartment configured to house the electrical equipment to be cooled. 7. The avionic bay according to claim 6, wherein the second pressure zone extends at a lower part of the electrical equipment, beneath one or more electronic boards of the electrical equipment to be cooled, along the extension dimension, which corresponds at least to a largest dimension of the one or more electronic boards. 8. The avionic bay according to claim 6 or 7, wherein the second pressure zone is disposed in contact with a given volume of the electrical equipment to be cooled, which is greater than a volume of the second pressure zone in contact with the first pressure zone. 9. The avionic bay according to claim 6, further comprising: a rack integrating the cooling air vein, the electrical equipment being disposed on the rack. 10. The avionic bay according to claim 9, wherein one or more of the second separation grille and the third separation grille includes apertures that are set off transversely in relation to respective apertures of one or more of the other grilles through which the cooling air passes along an axial direction. 11. The avionic bay according to claim 6, further comprising an electrical and mechanical adaptation tray, the first separation grille forming a part of the adaptation tray, and the electrical equipment being installed on the adaptation tray, the electrical equipment being able to be installed on the adaptation tray, over a base, of which the second separation grille forms a part. 12. An aircraft comprising at least one said avionic bay according to claim 6. 13. The avionic bay according to claim 6, wherein a first aeraulic joint forms the first pressure zone and a second aeraulic joint forms the second pressure zone. 14. The avionic bay according to claim 6, wherein the avionic bay is configured to have a pressure drop at one or more of an interface between the cooling air vein and the first pressure zone, an interface between the first pressure zone and the second pressure zone, and an interface between the second pressure zone and an interior of the electrical equipment. 15. The method according to claim 1, wherein the first pressure zone defines a first volume and the second pressure zone defines a second volume, the second volume being greater than the first volume. 16. The method according to claim 1, wherein the third separation grille has a length in the extension dimension greater than a length of at least one of the first separation grille and the second separation grille in the extension dimension. 17. The method according to claim 1, wherein the first separation grille is below the second separation grille, and the second separation grille is below the third separation grille. 18. The avionic bay according to claim 6, wherein the third separation grille has a length in the extension dimension greater than a length of at least one of the first separation grille and the second separation grille in the extension dimension. 19. The avionic bay according to claim 6, wherein portions of the first separation grille, the second separation grille, and the third separation grille overlap in an axial direction orthogonal to the extension dimension.
Whitson Frederick A. (Oconomowoc WI) Siebert William K. (West Bend WI) Raihala Kenneth B. (Racine WI), Filter for mounting on an avionic line replaceable unit.
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