IP Library Granted Patent US 9,115,592
Granted Patent B2
US 9,115,592 · App. 13/637,173 · Granted Aug 25, 2015

Sealing device for jet engine oil chamber

View Patent ↗
Loading inventors, assignments & file history…
Monitor This Case
Get email alerts when status or documents change.
Order Certified Copies
Most orders are placed with the USPTO same day — all within 24 business hours.
Order via The Patent Place →
Pre-filled with this patent's details
Quick Facts
Patent No.
US 9,115,592
App. No.
13/637,173
Granted
Aug 25, 2015
Kind
B2
Abstract

A sealing device for a chamber including at least one rotary member and at least one static member of a jet engine and can contain a lubricating oil droplet suspension. The sealing device includes at least one brush seal that includes juxtaposed strands and is set to ensure sealing between at least one rotary member and at least one stationary member, a mechanism to recover part of the oil suspended within the inner space of the chamber, and a mechanism to deliver the recovered oil. The delivery mechanism is set up to generate a flow of oil along the strands of the brush seal, the oil flow being oriented in the direction of the rotary member. The brush seal thus provides better resistance to coking.

Claims (15)

1. A turbojet comprising at least one enclosure that is formed by at least one rotary member and at least one static member of the turbojet, said enclosure containing a suspension of lubricating oil droplets, the enclosure comprising a sealing device comprising:

at least one brush seal including juxtaposed strands, radially oriented towards the rotary member, said strands being attached at one of their ends to a fixed member secured to the static member, the sealing device being configured to create a seal between the rotary member and the one static member to prevent oil from leaking out of the enclosure;

means for collecting some of the oil flowing along one wall of the enclosure; and

means for steering oil recovered from said one wall towards the fixed end of the strands of the brush seal,

wherein the brush seal is arranged to enable the passage of a gas flow from an exterior to an interior of the enclosure for evacuating the oil once the oil has reached the fixed end of the strands thereby to encourage the oil to flow along the strands.

2. The turbojet as claimed in claim 1 , wherein the means for steering includes at least one gravitational channel for guiding the oil from the means for collecting to the brush seal.

3. The turbojet as claimed in claim 2 , wherein the means for collecting includes, at a top of the turbojet, a tank for gravitational recovery of oil flowing along said one wall of the enclosure.

4. The turbojet as claimed in claim 3 , wherein said one wall is formed by a wall of a housing of the enclosure, said housing being conical and a diameter thereof decreasing from a downstream side to an upstream side.

5. The turbojet as claimed in claim 3 , wherein the tank is provided radially above the brush seal and takes the form of an enclosure presenting an upper face which is open.

6. The turbojet as claimed in claim 1 , wherein the rotary member comprises, inside the enclosure and close to the brush seal, a radial flange which is configured to receive the oil carried by the gas flow and to centrifugate the oil into the enclosure to suspend the oil again in the form of droplets.

7. The turbojet as claimed in claim 6 , wherein the radial flange forms a screen for the oil supplying the enclosure coming from at least one bearing of the rotary member, to prevent the lubricating oil from being projected directly onto the seal.

8. The turbojet as claimed in claim 7 , wherein the radial flange drives the oil which is carried to the radial flange by the gas flow into the enclosure, thereby centrifuging the oil into the enclosure where the oil is again suspended in the form of droplets.

9. The turbojet as claimed in claim 1 , wherein the enclosure comprises at least one bearing of the rotary member which is supplied with lubricating oil and which projects said lubricating oil into the enclosure to form a suspension of suspended droplets within the enclosure.

10. The turbojet as claimed in claim 9 , wherein the rotary member includes a radial flange which forms a screen for the oil supplying the enclosure coming from the at least one bearing, to prevent the lubricating oil from being projected directly onto the seal.

11. The turbojet as claimed in claim 10 , wherein the radial flange drives the oil which is carried to the radial flange by the gas flow into the enclosure, thereby centrifuging the oil into the enclosure where the oil is again suspended in the form of droplets.

Assignments (3)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Oct 3, 2012
From: GAUTHIER, GERARD PHILIPPE; MORREALE, SERGE RENE
To: SNECMA
Reel/Frame 029069/0304 →