IP Library Granted Patent US 7,625,175
Granted Patent B2
US 7,625,175 · App. 11/385,659 · Granted Dec 1, 2009

Link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine

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Quick Facts
Patent No.
US 7,625,175
App. No.
11/385,659
Granted
Dec 1, 2009
Kind
B2
Abstract

A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing and in orifices in the stator nozzle, each tube including a bellows between its ends and accommodating relative displacements and changes of alignment between the orifices in the casing and the orifices in the nozzle.

Claims (5)

1. A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing of the enclosure and in orifices in the stator nozzle, wherein a middle portion of each tube is formed by a metal bellows whose ends are secured to rings engaged in leaktight manner in the orifices of the casing and of the nozzle, respectively, wherein the bellows is resiliently prestressed so as to urge the rings against surfaces of the orifices of the casing and of the nozzle, respectively, wherein the ring that is engaged in the orifice of the nozzle has a frustoconical outside surface which is in axial abutment against a complementary frustoconical surface of the orifice of the nozzle.

2. A device according to claim 1 , wherein each ring engaged in the orifice of the casing is cylindrical and is pressed against a sealing washer mounted in an annular groove in the inner cylindrical surface of the orifice in the casing.

3. A turbomachine including nozzles connected to outer and inner enclosures by link device according to claim 1 .

4. A link device between an enclosure for passing cooling air and a stator nozzle in a turbomachine, the device comprising metal tubes having their ends mounted in leaktight manner in orifices in a casing of the enclosure and in orifices in the stator nozzle, wherein a middle portion of each tube is formed by a metal bellows whose ends are secured to rings engaged in leaktight manner in the orifices of the casing and of the nozzle, respectively, wherein each ring engaged in the orifice of the casing is cylindrical and is in abutment against a sealing washer mounted in an annular groove in the inner cylindrical surface of the orifice in the casing by the bellows which is resiliently prestressed, and wherein the ring that is engaged in the orifice of the nozzle has a frustoconical outside surface which is in axial abutment against a complementary frustoconical surface of the orifice of the nozzle.

5. A device according to claim 1 , wherein the bellows is resiliently prestressed axially to urge said rings towards the casing and the nozzle, respectively.

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 Mar 22, 2006
From: DERVAUX, ALEXANDRE; BERMOND, SABINE
To: SNECMA
Reel/Frame 017716/0559 →