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AssigneeSafran Aircraft Engines
InventorsMichel Slusarz, Pierre Guillaume Auzillon, Patrice Eneau, Léandre Ostino
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An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4′) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.
An aircraft turbine engine blade, comprising at least one inner cavity configured to circulate a ventilation air flow, the cavity comprising a wall that comprises first projecting elements oriented in at least one first direction and forming air flow disrupters, the wall further comprising at least one second projecting element oriented in at least one second direction different from the first direction, wherein the second projecting element and at least one of the first projecting elements overlap each other in an area, at least one of the first projecting elements overlapping the second projecting element and having a height greater than a height of the second projecting element in said area and which is greater than that of the other first projecting elements of the wall, to retain a disruptive function over an entire length thereof, and wherein only one of the first projecting elements overlaps said second projecting element and forms a cross with the second projecting element.
An aircraft turbine engine blade, comprising at least one inner cavity configured to circulate a ventilation air flow, the cavity comprising a wall that comprises first projecting elements oriented in at least one first direction and forming air flow disrupters, the wall further comprising at least one second projecting element oriented in at least one second direction different from the first direction, wherein the second projecting element and at least one of the first projecting elements overlap each other in an area, at least one of the first projecting elements overlapping the second projecting element and having a height greater than a height of the second projecting element in said area and which is greater than that of the other first projecting elements of the wall, to retain a disruptive function over an entire length thereof, and wherein the height of the second projecting element and of the first projecting elements is a dimension of these elements measured along a direction normal to the surface of the wall over which they are projected, and wherein only one of the first projecting elements overlaps said second projecting element and forms a cross with the second projecting element.
An aircraft turbine engine blade, comprising at least one inner cavity configured to circulate a ventilation air flow, the cavity comprising a wall that comprises first projecting elements oriented in at least one first direction and forming air flow disrupters, the wall further comprising at least one second projecting element oriented in at least one second direction different from the first direction, wherein the second projecting element and at least one of the first projecting elements overlap each other in an area, at least one of the first projecting elements overlapping the second projecting element and having a height greater than a height of the second projecting element in said area and which is greater than that of the other first projecting elements of the wall which do not overlap the second projecting element, to retain a disruptive function over an entire length thereof, and wherein only one of the first projecting elements overlaps said second projecting element and forms a cross with the second projecting element.
Dependencies are inferred from the claim text.