IP Library Granted Patent US 11,585,236
Granted Patent B2
US 11,585,236 · App. 16/982,795 · Granted Feb 21, 2023

Turbojet bearing support produced by additive manufacturing

Inventors: Dimitri Daniel Gabriel Marquie (Moissy-Cramayel, FR); Adrien Jacques Philippe Fabre (Moissy-Cramayel, FR); Frédéric Patard (Moissy-Cramayel, FR); Pierre Jean-Baptiste Metge (Moissy-Cramayel, FR)
Assignee: SAFRAN AIRCRAFT ENGINES
F01D25/164F01D25/183B33Y80/00F05D2220/3213F05D2230/23F05D2240/50F05D2260/98
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Quick Facts
Patent No.
US 11,585,236
App. No.
16/982,795
Granted
Feb 21, 2023
Kind
B2
Abstract

A bearing support designed to be secured to a stationary turbojet element for supporting a journal, including a cone which widens from a central portion for supporting the journal to a portion for securing to the stationary element, a cylindrical body extending the portion for securing to the stationary element while surrounding the cone, an upstream skirt carried by the cone for defining an upstream enclosure for the central portion, and at least one downstream revolution element carried by the cone for defining a downstream enclosure for the central portion. The bearing support can be made as a single part produced by additive manufacturing.

Claims (15)

1. A bearing support, intended to be secured to a stationary turbojet element for supporting a journal, comprising:

a tapered element which widens from a central portion for supporting the journal to a portion for securing to the stationary element;

a cylindrical body extending the portion for securing to the stationary element while surrounding the tapered element;

an upstream skirt carried by the tapered element for defining an upstream enclosure for the central portion; and

at least one downstream revolution element carried by the tapered element for defining a downstream enclosure for the central portion,

wherein said bearing support is made as a single part produced by additive manufacturing.

2. The bearing support according to claim 1 , comprising an upstream support for a segmented radial seal extending the upstream skirt.

3. The bearing support according to claim 1 , comprising a nozzle protruding from an inner face of the upstream skirt in the upstream enclosure to cool and lubricate the upstream enclosure.

4. The bearing support according to claim 1 , comprising a sleeve intended to receive an outer roller bearing ring surrounding the journal, said sleeve being surrounded by the central portion, and wherein the sleeve is extended by a squirrel cage through which the sleeve is rigidly secured to an upstream end of the upstream skirt.

5. The bearing support according to claim 4 , wherein the sleeve is radially spaced from the central portion that surrounds the sleeve to define an annular space intended to receive a hydraulic flow.

6. The bearing support according to claim 5 , comprising a feed channel of the annular space surrounding the sleeve, said channel passing through the tapered element.

7. The bearing support according to claim 1 , comprising an oil return path connected to at least one of the upstream enclosure and the downstream enclosure via a manifold, said oil return path passing through the tapered element.

8. A turbojet comprising a bearing support according to claim 1 .

9. The bearing support according to claim 5 , wherein the central portion comprises an annular element extending the tapered element, the sleeve extends inside the annular element, and the sleeve is not directly connected to the annular element.

10. The bearing support according to claim 7 , wherein an upstream end of the oil return path is located substantially in line with the portion for securing to the stationary element.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Sep 21, 2020
From: MARQUIE, DIMITRI DANIEL GABRIEL; FABRE, ADRIEN JACQUES PHILIPPE; PATARD, FRÉDÉRIC; METGE, PIERRE JEAN-BAPTISTE
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 053831/0684 →
Priority Claims (1)
FR 18 52557 · Mar 23, 2018 · national
Continuity (1)
Related Publication 20210062679A1 · Mar 4, 2021