GUIDE VANE, ASSOCIATED TURBOMACHINE AND ASSOCIATED MANUFACTURING METHOD

The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage (50a) delimited in part by an intrados wall and an extrados wall (...

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Bibliographische Detailangaben
Hauptverfasser:	MARQUIE DIMITRI DANIEL GABRIEL, LEGUERY GEOFFRAY HENRI ROBERT, SENEJOUX PIERRE FRANCOIS
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEAT EXCHANGE IN GENERAL HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage (50a) delimited in part by an intrados wall and an extrados wall (72) of the vane, there being flow-disturbing lugs (80), made as one piece with one of the intrados and extrados walls (72), passing across the passage. According to the invention, in any plane of section passing orthogonally through the lugs (80), the space (94) defined between these lugs has a geometry defined exclusively by a set of annulus shapes (92) of the same dimensions, partially overlapping one another and each in part delimiting at least two of these lugs (80). 本发明涉及一种导向叶片，该导向叶片旨在被布置在飞行器的涵道涡轮机风扇的全部或部分空气流中，叶片包括空气动力学部件，该空气动力学部件配备有由叶片的拱腹壁和拱背壁(72)部分地界定的至少一个内部润滑剂冷却通道(50a)，存在与穿过通道的拱腹壁和拱背壁(72)之一制成一体件的扰流凸耳(80)。根据本发明，在正交地穿过凸耳(80)的任何截面中，在这些凸耳之间限定的空间(94)具有仅由具有相同尺寸的一组环形形状(92)限定的几何形状，这些环形形状彼此部分地重叠并且每个环形形状部分地界定这些凸耳(80)