Lubricant distributor for turbomachinery and turbomachinery equipped with such a distributor

FR3162058A1Pending Publication Date: 2025-11-14SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
FR2024004843
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-05-10
Publication Date
2025-11-14

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Abstract

Lubricant distributor (20) comprising: a. a flange (21) extending around a first tube (22); b. a second tube (23) substantially coaxial with the first tube (22) and having a diameter smaller than the diameter of the first tube (22); c. a third tube (24) connected to the first tube at their first ends, said third tube (24) passing through the wall of the first tube (22) and forming an angle with the second tube (23); the first tube (22) forming a first lubricant flow circuit; the second tube (23) and the third tube (24) forming a second lubricant flow circuit. Figure for the abbreviation: Fig 3
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Claims

lubricant recovery (3) and an auxiliary lubricant reservoir (6), the lubrication housing (1) being configured to ensure the recirculation of the recovered lubricant, the hub housing being disposed on a first side of the lubrication housing (1), the drain box being disposed on a second side of the lubrication housing (1), the lubricant recovery area (3) and the auxiliary lubricant reservoir (6) being disposed at the base of one of the support arms (15), characterized in that it comprises a lubricant distributor (20) as claimed in any one of claims 1 to 6, disposed at the base of said support arm (15) such that the flange (21) is disposed bearing on the external surface of the first side of the lubrication housing (1) in a hole opening into the lubricant recovery area (3),the turbomachine further comprising a drain line (40) allowing the recirculation of the lubricant contained in the auxiliary lubricant reservoir (6) connected to the drain interface (25) and an upstream drain (41) of the drain line from the hub housing connected to the drain interface (26) in order to convey the lubricant recovered from the hub housing to the drain box.

8. Turbomachine according to claim 7, wherein the discharge interface (25) and the drain interface (26) are substantially collinear.

9. Turbomachine according to any one of claims 7 to 9, wherein the second tube (23), substantially collinear with the first tube (22), extends through the lubricant recovery zone (3) in front of the mouth of the pipe (6a) leading to the auxiliary lubricant reservoir (6) to a hole (32) formed in the opposite wall of the lubricant recovery zone (3), the hole (32) formed in the opposite wall of the lubricant recovery zone (3) comprising a bore designed to facilitate the insertion of the second tube (23) into the hole (32) formed in the opposite wall of the lubricant recovery zone (3).

10. Turbomachine according to claim 9, wherein the hole (32) formed in the opposite wall of the lubricant recovery zone (3) includes a nipple (33) designed to provide the interface between the second tube (23) and a downstream drain (34) to the drain box. [Fig. 3] [Fig. 5] 22 21

Citation Information

Patent Citations

  • Tubular oil gas water three -phase separator

    CN205269228U

  • DRAINAGE DEVICE FOR AN AIRCRAFT TURBOMACHINE

    FR3108934A1

  • Heat-exchanger

    JP1999325761A

  • Drain pipe arrangement and gas turbine engine comprising a drain pipe arrangement

    US20150152786A1