Single piece part i.e. casting part, for intermediate casing hub of e.g. turbojet engine, of aircraft, has deflecting surface whose radial internal end partially defines separation nozzle, where surface is extended to external end

The piece (70) has a portion of downstream flange (42) of a hub (36), and a portion of an internal ferrule (38) of the hub including a separation nozzle (60) partially defined by an external delimitation surface (62) of a primary flow (22) of a turbo shaft engine. A deflecting surface (65) guides th...

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Bibliographische Detailangaben
Hauptverfasser:	SEVI GUILLAUME, COMBIER FLORENT
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	The piece (70) has a portion of downstream flange (42) of a hub (36), and a portion of an internal ferrule (38) of the hub including a separation nozzle (60) partially defined by an external delimitation surface (62) of a primary flow (22) of a turbo shaft engine. A deflecting surface (65) guides the air and includes a radial internal end (65a) partially defining the separation nozzle. The deflecting surface is extended to a radial external end (65b) formed by an upstream surface of the downstream flange. L'invention concerne une pièce (70) réalisée d'un seul tenant pour moyeu (36) de carter intermédiaire de turbomachine d'aéronef, comprenant : - au moins une partie d'un flasque aval (42) du moyeu ; - au moins une partie d'une virole interne (38) du moyeu comprenant au moins un bec de séparation (60) en partie défini par une surface de délimitation externe (62) d'un flux primaire (22) de turbomachine. Selon l'invention, la pièce comprend de plus une surface déflectrice (65) pour le guidage de l'air, cette surface comprenant une extrémité radiale interne (65a) définissant en partie le bec (60), et se prolongeant jusqu'à une extrémité radiale externe (65b) formée par une surface amont du flasque aval (42).