Turbomachine comprising a ventilation system

Patent metadata

Field	Value
Publication number	US-10364691-B2
Application number	US-201615156660-A
Country	US
Kind code	B2
Filing date	May 17, 2016
Priority date	May 21, 2015
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

A turbomachine subassembly has a radially inner shell and a radially outer shell of an annular gas flow path. A radial arm extends radially between the radially inner and outer shells and delimits an isolated volume which is connected to an inner volume of a chamber partly delimited by the radially inner shell. A segment of a conduit extends radially in the isolated volume, and a ventilation air supply source is connected to supply ventilation air to the isolated volume, whereby ventilation air may be supplied to the chamber through the isolated volume. An external radial end of the radial arm supports a first connection box that closes it off. The internal volume of the radial arm communicates with the ventilation air supply source. An external cylindrical wall of the first connection box fits inside an internal cylindrical wall of the external radial end of the radial arm.

First claim

The invention claimed is:

1. A turbomachine subassembly comprising:
a radially inner shell and a radially outer shell which radially delimit, between the radially inner shell and the radially outer shell, an annular gas flow path,
a chamber delimited at least partly by the radially inner shell,
at least one radial arm that extends radially between the radially inner shell and the radially outer shell, wherein the at least one radial arm delimits an internal isolated volume of the annular flow path, which isolated volume is connected to an inner volume of said chamber, and wherein a segment of at least one conduit extends radially in said isolated volume, and
a ventilation air supply source connected to supply ventilation air to said isolated volume delimited by said at least one radial arm, whereby ventilation air may be supplied to the chamber delimited at least partly by the inner shell through the isolated volume delimited by said at least one radial arm,
wherein a radial outer end of the at least one radial arm supports a first connection box that closes off the radial outer end of the at least one radial arm,
wherein a connection of the segment of the at least one conduit connects the segment to a remainder of the at least one conduit,
wherein the isolated volume of the at least one radial arm communicates with the ventilation air supply source, and
wherein the first connection box comprises an external cylindrical wall that fits inside an internal cylindrical wall of the radial outer end of the at least one radial arm.

2. The subassembly according to claim 1 , wherein the external cylindrical wall of the first connection box and the internal cylindrical wall of the radial outer end of the at least one radial arm are surfaces of revolution.

3. The subassembly according to claim 1 , wherein the first connection box is mounted to be free to slide radially relative to the radial outer end of the at least one radial arm.

4. The subassembly according to claim 1 , wherein a radial inner end of said at least one radial arm opens directly into the chamber delimited at least partly by the radially inner shell.

5. The subassembly according to claim 4 , further comprising a second connection box that is installed at the radial inner end of the at least one radial arm and that is radially offset inwards relative to the radial inner end of the at least one radial arm.

6. The subassembly according to claim 5 , wherein there are a plurality of said radial arms, further comprising a support ring on which second connection boxes of all of said plurality of radial arms are installed.

7. The subassembly according to claim 5 , wherein the second connection box comprises a first channel oriented principally along the radial direction, to which the internal radial end of the corresponding segment of conduit is connected, and a second channel oriented principally parallel to a main axis of the turbomachine, which second channel extends the first channel and is connected to the remainder of the conduit.

8. An aircraft turbomachine, comprising the subassembly of claim 1 , wherein the ventilation air supply source draws off air from a secondary flow path of the turbomachine.

Assignees

• Safran Aircraft Engines

Inventors

• Curlier Augustin Marc Michel
• Aussedat Nicolas

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title