IP Library › Granted Patent US 11,686,216
Granted Patent B2
US 11,686,216 · App. 17/597,065 · Granted Jun 27, 2023

Turbomachine output bearing support

Inventors: Nicolas Ovaere (Moissy-Cramayel, FR); Fabien Stéphane Garnier (Moissy-Cramayel, FR); Arnaud Lasantha Genilier (Moissy-Cramayel, FR); Pierre Jean-Baptiste Metge (Moissy-Cramayel, FR)
Assignee: SAFRAN AIRCRAFT ENGINES
F01D25/162F01D25/18F01D25/24F05D2220/32F05D2230/31F05D2240/50F05D2260/98
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Quick Facts
Patent No.
US 11,686,216
App. No.
17/597,065
Granted
Jun 27, 2023
Kind
B2
Abstract

Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

Claims (8)

1. A turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall and having an inner side and an outer side, an annular outer wall arranged to the outer side of the inner wall, and a twist support, the inner wall comprising a first section having a first substantially frustoconical form extending according to the axial direction and having the inner side and the outer side, the first section having a first axial end provided with a first attachment flange and a second axial end opposite according to the axial direction to the first axial end, provided with a bearing support section, the first section carrying on the inner side an inner section forming a second attachment flange, the twist support being carried by the inner wall on the outer side.

2. The turbomachine output bearing support according to claim 1 , wherein the outer wall has a second substantially frustoconical form extending according to the axial direction and having a third axial end attached to the inner wall on the outer side of the inner wall, and a fourth axial end, opposite the second axial end according to the axial direction, forming a collector ring.

3. The turbomachine output bearing support according to claim 2 , comprising at least one air exhaust duct extending on the external side of the outer wall and fluidically connecting the internal side of the inner wall and the collector ring.

4. The turbomachine output bearing support according to claim 3 , comprising three air exhaust ducts uniformly distributed around the axial direction.

5. The turbomachine output bearing support according to claim 3 , wherein the at least one air exhaust duct has an air outlet opening arranged in the inner wall.

6. The turbomachine output bearing support according to claim 1 , comprising an oil drainage duct.

7. The turbomachine output bearing support according to claim 6 , wherein the oil drainage duct extends on the external side of the outer wall and has a first intake arranged in the collector ring, a second intake arranged in the outer wall and opening into a space formed between the twist support and the outer wall, and an output terminating to the internal side of the inner wall.

8. A manufacturing process of a turbomachine output bearing support according to claim 1 , comprising at least one additive manufacturing step.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Dec 27, 2021
From: OVAERE, NICOLAS; GARNIER, FABIEN STÉPHANE; GENILIER, ARNAUD LASANTHA; METGE, PIERRE JEAN-BAPTISTE
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 058480/0233 →
Priority Claims (1)
FR 1906933 · Jun 26, 2019 · national
Continuity (1)
Related Publication 20220235672A1 · Jul 28, 2022