Assembly comprising an exhaust case and a downstream rotationally symmetrical part

Patent metadata

Field	Value
Publication number	US-11053890-B2
Application number	US-201615580496-A
Country	US
Kind code	B2
Filing date	Jun 10, 2016
Priority date	Jun 11, 2015
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

The invention relates to an assembly comprising: a turbomachine exhaust case ( 110 ) that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part ( 130 ) that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbomachine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread ( 131, 115 ), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.

First claim

The invention claimed is:

1. An assembly of a turbomachine comprising:
an exhaust case comprising:
an outer shroud;
an inner shroud concentric with the outer shroud and extending inside the outer shroud, a first circumferential thread being formed in one of the inner shroud and the outer shroud; and

a plurality of arms extending radially between the inner shroud and the outer shroud;
an annular part, a second circumferential thread being formed in the annular part, the second circumferential thread cooperating with the first circumferential thread to allow mounting by screwing of the annular part on the one of the inner shroud and the outer shroud wherein the first circumferential thread is formed, downstream of the exhaust case with respect to an air flow in the turbomachine; and
a stopping system comprising:
a groove arranged adjacent to the first circumferential thread and having a bottom;
a plurality of threaded openings extending through the annular part and suitable for being located facing the groove when the annular part is screwed on the exhaust case; and
a plurality of screws, each screw of the plurality of screws having the end, the plurality of screws being suitable for being screwed into the plurality of threaded openings so that the end of each screw of the plurality of screws comes into abutment against the bottom of the groove in order for the annular part to be stopped in axial translation relative to the exhaust case.

2. The assembly of claim 1 , wherein the first circumferential thread formed on a radially outer surface of the one of the inner shroud and the outer shroud.

3. The assembly of claim 1 , wherein the groove is circumferential.

4. The assembly of claim 1 , wherein the annular part is a mixer or an exhaust nozzle mounted on the outer shroud.

5. The assembly of claim 1 , wherein the annular part is an exhaust cone mounted on the inner shroud.

6. The assembly of claim 1 , wherein the annular part is an exhaust cone mounted on the inner shroud; wherein each screw of the plurality of screws is further formed to be able to be integrally contained in a volume consisting of an opening of the plurality of the threaded openings and the groove.

7. A turbomachine, comprising an assembly of claim 1 .

8. The assembly of claim 1 , wherein the first circumferential thread is formed on a radially outer surface of the one of the inner shroud and the outer shroud, in proximity to a downstream edge of the radially outer surface.

9. The assembly of claim 1 , wherein the first circumferential thread extends over two to ten turns of the one of the inner shroud and the outer shroud.

10. The assembly of claim 1 , wherein a third circumferential thread is formed in the other of the inner shroud and the outer shroud to screw a mixer or an exhaust nozzle on the outer shroud and an exhaust cone on the inner shroud.

11. The assembly of claim 1 , wherein the second circumferential thread is formed on a radially inner surface of the annular part.

12. The assembly of claim 1 , wherein the first circumferential thread and the second circumferential thread are made by milling.

13. The assembly of claim 1 , wherein the groove comprises a plurality of circular sector sections.

Assignees

• Safran Aircraft Engines

Inventors

• De Sousa Mario Cesar
• Debray Benoit Argemiro Matthieu
• Fouquet Dominique Michel
• Ghosarossian-Prillieux Gregory
• Noel Frederic

Classifications

• F02K1/48

  Corrugated nozzles · CPC title

• F01D25/162

  Bearing supports · CPC title

• F02K1/04

  Mounting of an exhaust cone in the jet pipe · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02K1/386

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title