Back to results
US 2012/0237332 A1Published application
Fluid-cooling device for a turbine engine propulsive unit
AssigneeAirbus Operations GmbH
InventorsGuillaume Bulin, Ralf-Henning Stolte
Life of this patent
Estimating the term…
Loading patent…
Loading patent…
AssigneeAirbus Operations GmbH
InventorsGuillaume Bulin, Ralf-Henning Stolte
Estimating the term…
The invention relates to a fluid cooling device (1) for the propulsion unit of an aircraft of the so-called propfan type, comprising a compressed air intake (11) at the air compressor of the turbomachine (8), an air vein (13) capable of conveying the collected compressed air to a cooler (14), means of conveying the heat of the lubricant to the cooler, said cooler (14) comprising firstly, a matrix body (15) provided with a plurality of ducts (20) for a cooling agent, said ducts (20) extending along a first so-called inner surface (17) up to a second so-called outer surface (16) of the matrix body (15), such that the collected pressurized air serving as a cooling agent can pass through the matrix body (15), the matrix body (15) of the cooler (14) forming a portion of the outer skin (6) of the propulsion unit, and, secondly, a set of fins (18) extending from the outer surface (16) towards the outside of the propulsion unit, and oriented mainly parallel to the air flow direction (X) when the aircraft is in flight.
Fluid cooling device for the propulsion unit of an aircraft of the so-called propfan type, said propulsion unit comprising a turbomachine (8) that drives in rotation at least one rotor, said turbomachine (8) being supplied with outside air by an air inlet (7), said turbomachine (8) comprising a compressor with at least two stages, and generating heating of a lubricant during its operation,
Cooling device (1) according to any one of the preceding claims, characterized in that the matrix body (15) of the cooler (14) forms a portion of the outer skin (6) of the propulsion unit.
Cooling device (1) according to any one of the preceding claims, characterized in that the pressurized air intake (11) is positioned downstream of the 1st or 2nd stage of the air compressor of the turbomachine (8).
Cooling device (1) according to any one of the preceding claims, characterized in that it comprises an additional air inlet positioned substantially forward of the propulsion unit.
Cooling device (1) according to any one of the preceding claims, characterized in that the matrix body (15) comprises a plurality of strips delimiting the ducts (20).
Cooling device (1) according to any one of the preceding claims, characterized in that the ducts (20) of the matrix body (15) are oriented substantially perpendicular to the outer surface (16) of the matrix body (15).
Cooling device (1) according to any one of the preceding claims, characterized in that it comprises means of controlling (19) the flow of pressurized air passing through the ducts (20) of the matrix body (15) of the cooler (14).
Aircraft comprising a device according to any one of the preceding claims.
Dependencies are inferred from the claim text.