Method for holding an adapter piece on a tubular housing of a turbo engine, and corresponding adapter piece and holding system

Patent metadata

Field	Value
Publication number	US-9834312-B2
Application number	US-201314380470-A
Country	US
Kind code	B2
Filing date	Feb 27, 2013
Priority date	Feb 28, 2012
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

An adapting part is designed to be held on a casing of a turbo-engine, partially covering the casing. The adapting part includes, in the extension of one of its axial ends, a first connector to engage with a first complementary connector associated with the casing to form a sliding connection. The adapting part also includes, at its other axial end, a second connector to be secured to a second complementary connector associated with the casing to form a rigid connection.

First claim

The invention claimed is:

1. An adapting part designed to transmit forces between a tubular casing of a turbo-engine and a suspension of the turbo-engine to a pylon of an aircraft, by partially covering the tubular casing, the adapting part comprising:
a hoop portion of predetermined angular sector;
suspension devises arranged on a face of the hoop portion which faces outwards and designed to connect the adapting part to the suspension;
in an extension of a first axial end of the adapting part, a projecting tab extending axially from the hoop portion and configured to engage with a groove of a connecting member associated with said tubular casing to form an axial sliding connection; and
at a second axial end of the adapting part, a flange configured to be secured to a flange of said tubular casing to form a rigid connection,
wherein the projecting tab is entirely circular or extends circumferentially over the predetermined angular sector.

2. The adapting part as claimed in claim 1 , wherein the flange is entirely circular or extends circumferentially over the predetermined angular sector.

3. The adapting part as claimed in claim 1 , wherein the predetermined angular sector of the hoop portion is equal to 120°.

4. A system, comprising:
an adapting part comprising:
a hoop portion of predetermined angular sector;
suspension devises arranged on a face of the hoop portion which faces outwards and designed to connect the adapting part to the suspension;
in an extension of a first axial end of the adapting part, a projecting tab extending axially from the hoop portion; and
at a second axial end of the adapting part, a flange,
wherein the projecting tab is entirely circular or extends circumferentially over the predetermined angular sector:

a tubular casing of a turbo-engine arranged for holding, to the tubular casing, the adapting part;
a groove of a connecting member associated with said tubular casing which engages with the projecting tab of the adapting part to form an axial sliding connection in a first axial end of the tubular casing; and
a flange of said tubular casing which engages with the flange of the adapting part to form a rigid connection in a second axial end of the tubular casing.

5. The system as claimed in claim 4 , wherein the connecting member is fitted on one end flange of said tubular casing.

6. The system as claimed in claim 4 , wherein the connecting member radially extends to one end flange of said tubular casing.

7. A suspension for a turbo-engine on a pylon of an aircraft, comprising:
a front suspension bracket mounted on an intermediate casing of the turbo-engine;
a rear suspension bracket mounted on an inter-turbine casing of the turbo-engine; and
wherein an adapting part as claimed in claim 1 connects the rear suspension bracket to the inter-turbine casing of the turbo-engine.

8. A turbo-engine attached to a pylon of an aircraft, comprising:
a front suspension bracket mounted on an intermediate casing of the turbo-engine;
a rear suspension bracket mounted on an inter-turbine casing of the turbo-engine; and
a system as claimed in claim 4 ,
wherein the adapting part of the system connects the rear suspension bracket to the inter-turbine casing of the turbo-engine.

Assignees

• Snecma

Inventors

• Beaujard Antoine Jean-Philippe
• Besnard Maryline

Classifications

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• Y10T29/49826

  Assembling or joining · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• Y10T403/32229

  Articulate joint is a slide · CPC title