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An ejector nozzle tube, having along its length an essentially constant, essentially oval hollow cross-section, with a leading edge nozzle, having a rounded exterior cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube. The leading edge nozzle includes a plurality of

An ejector nozzle tube, having along its length an essentially constant, essentially oval hollow cross-section, with a leading edge nozzle, having a rounded exterior cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube. The leading edge nozzle includes a plurality of grooves issuing to the top and bottom sides of the ejector nozzle tube and connecting to an interior of the ejector nozzle tube formed by the hollow profile. An aircraft engine has an optimized oil heat exchanger with at least one oil cooler disposed in a trailing-edge area of an aerofoil-type structure, with at least one flow entrance area being provided to supply ambient air to the oil cooler disposed in a flow duct. The ejector nozzle tube can be arranged downstream of the oil cooler in the flow duct.

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1. An ejector nozzle tube intended to be positioned longitudinally in an aircraft airfoil having a duct, downstream of an inlet of the duct and an oil cooler heat exchanger located within the duct, comprising: a main body having an essentially constant, essentially oval cross-section along a length

1. An ejector nozzle tube intended to be positioned longitudinally in an aircraft airfoil having a duct, downstream of an inlet of the duct and an oil cooler heat exchanger located within the duct, comprising: a main body having an essentially constant, essentially oval cross-section along a length thereof and having a hollow interior, the essentially oval cross-section having a first narrow side, a second narrow side opposite the first narrow side and a wider central portion positioned between the first narrow side and the second narrow side, the first narrow side establishing a leading edge area and the second narrow side establishing a trailing edge area such that a fluid flow past the main body flows in a downstream direction from the leading edge area to the trailing edge area;a leading edge lip element having a rounded exterior cross-section and being attached to the main body at the leading edge area, the leading edge lip element including a plurality of grooves positioned spaced apart along the length of the main body and connecting to the hollow interior to form a plurality of nozzles for fluid passage between the hollow interior and an exterior of the main body, wherein the ejector nozzle tube is configured to receive bleed air from the engine and pass the bleed air along the length of the ejector nozzle tube to the plurality of nozzles, the plurality of nozzles issuing the bleed air to an exterior surface of the ejector nozzle tube at the leading edge area and in the downstream direction to form a near surface flow along an exterior surface of the main body from the leading edge lip element toward the trailing edge area. 2. The ejector nozzle tube of claim 1, wherein the main body of the ejector nozzle tube has a smaller wall thickness than the leading edge lip element. 3. The ejector nozzle tube of claim 2, further comprising a plurality of connections between the main body and the leading edge lip element positioned between the plurality of grooves. 4. The ejector nozzle tube of claim 1, wherein the grooves are arranged in the sectional planes of the ejector nozzle tube that are perpendicular to a longitudinal axis of the ejector nozzle tube. 5. The ejector nozzle tube of claim 4, wherein the main body of the ejector nozzle tube is made of sheet metal, with at least a portion of the leading edge area being open to the interior, the leading edge lip element having a thicker wall thickness than a wall thickness of the main body. 6. The ejector nozzle tube of claim 5, further comprising a plurality of weld connections between the main body and the leading edge lip element positioned between the plurality of grooves. 7. The ejector nozzle tube of claim 4, further comprising a plurality of connections between the main body and the leading edge lip element positioned between the plurality of grooves. 8. The ejector nozzle tube of claim 1, wherein the main body of the ejector nozzle tube is made of sheet metal, with at least a portion of the leading edge area being open to the interior, the leading edge lip element having a thicker wall thickness than a wall thickness of the main body. 9. The ejector nozzle tube of claim 8, further comprising a plurality of weld connections between the main body and the leading edge lip element positioned between the plurality of grooves. 10. The ejector nozzle tube of claim 1, further comprising a plurality of connections between the main body and the leading edge lip element positioned between the plurality of grooves. 11. A cooling arrangement for an aircraft engine comprising: a flow duct positioned in an airfoil structure;an oil heat exchanger with at least one oil cooler positioned in the flow duct in a trailing edge area of the airfoil structure;the flow duct including at least one flow entrance area for supplying a flow of ambient air to the oil cooler;an ejector nozzle tube positioned downstream of the oil cooler in the flow duct and extending in a longitudinal direction in the airfoil structure;the ejector nozzle tube comprising:a main body having an essentially constant, essentially oval cross-section along a length thereof and having a hollow interior, the essentially oval cross-section having a first narrow side, a second narrow side opposite the first narrow side and a wider central portion positioned between the first narrow side and the second narrow side, the first narrow side establishing a leading edge area facing in an upstream direction of the flow and the second narrow side establishing a trailing edge area facing in a downstream direction of the flow;a leading edge lip element having a rounded exterior cross-section and being attached to the main body at the leading edge area, the leading edge lip element including a plurality of grooves positioned spaced apart along the length of the main body and connecting to the hollow interior to form a plurality of nozzles for fluid passage between the hollow interior and an exterior of the main body, wherein the ejector nozzle tube is configured to receive bleed air from the engine and pass the bleed air along the length of the ejector nozzle tube to the plurality of nozzles, the plurality of nozzles issuing the bleed air to an exterior surface of the ejector nozzle tube at the leading edge area and in the downstream direction to form a near surface flow along an exterior surface of the main body from the leading edge lip element toward the trailing edge area. 12. The cooling arrangement in accordance with claim 11, wherein the flow duct downstream of the oil cooler is formed by at least one variable wall element. 13. The cooling arrangement in accordance with claim 12, wherein the at least one variable wall element includes at least one aerodynamically contoured pivotal flap. 14. The cooling arrangement in accordance with claim 13, wherein the at least one variable wall element includes an upper and a lower contoured pivotal flap opposing one another. 15. The cooling arrangement of claim 14, wherein the main body of the ejector nozzle tube is made of sheet metal, with at least a portion of the leading edge area being open to the interior, the leading edge lip element having a thicker wall thickness than a wall thickness of the main body. 16. The cooling arrangement of claim 15, further comprising a plurality of weld connections between the main body and the leading edge lip element positioned between the plurality of grooves. 17. The cooling arrangement of claim 11, wherein the main body of the ejector nozzle tube is made of sheet metal, with at least a portion of the leading edge area being open to the interior, the leading edge lip element having a thicker wall thickness than a wall thickness of the main body. 18. The cooling arrangement of claim 17, further comprising a plurality of weld connections between the main body and the leading edge lip element positioned between the plurality of grooves. 19. The cooling arrangement of claim 11, wherein the main body of the ejector nozzle tube has a smaller wall thickness than the leading edge lip element. 20. The cooling arrangement of claim 19, further comprising a plurality of connections between the main body and the leading edge lip element positioned between the plurality of grooves.