Metallisation of an electrically insulating housing of an aeronautic engine

Patent metadata

Field	Value
Publication number	US-9919805-B2
Application number	US-201414528467-A
Country	US
Kind code	B2
Filing date	Oct 30, 2014
Priority date	Oct 30, 2013
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

An aeronautic engine including: a housing made of electrically insulating material and including at least one metallic piece; a structural piece of the engine including metallic material and connected to the housing; and an equipment fixed to the housing, is provided. The equipment is connected to the structural piece by the metallic piece by an electrically conductive connecting path.

First claim

The invention claimed is:

1. An aeronautic engine, comprising:
a housing, made of electrically insulating material, said housing comprising at least one metallic piece, and
a structural piece of the engine, comprising metallic material and connected to the housing,
an equipment, fixed to the housing,
wherein the equipment is electrically connected to the structural piece through an intermediary of the metallic piece due to an electrically conductive connecting path, and
wherein the connecting path comprises successively the following elements:
a metal-metal contact between the equipment and a metallic support, a ground braid between the metallic support and the metallic piece of the housing and a ground braid between the metallic piece of the housing and the structural piece, or
a metal-metal contact between the equipment and the metallic support, a metal-metal contact between the metallic support and the metallic piece of the housing and a ground braid between the metallic piece of the housing and the structural piece, or
a ground braid between the equipment and the metallic piece of the housing and a ground braid between the metallic piece of the housing and the structural piece.

2. The aeronautic engine according to claim 1 , wherein the metallic piece of the housing comprises at least one of a flange, a slave arm, an inspection door threshold, and an equipment threshold.

3. The aeronautic engine according to claim 1 , further comprising a connecting flange, adapted to fix the housing to the structural piece, and wherein the connecting path is connected to the structural piece by said connecting flange.

4. The aeronautic engine according to claim 3 , wherein the metallic support fixed both to the equipment and the connecting flange.

5. The aeronautic engine according to claim 1 , wherein the housing is an OFD housing and the structural piece is a fan housing.

6. The aeronautic engine according to claim 5 , further comprising a thrust reverser, said thrust reverser being connected to the metallic piece of the OFD housing with an electrically conductive connecting path.

7. The aeronautic engine according to claim 1 , wherein the equipment comprises at least one of an ignition box, a sensor, a fuel-oil heat exchanger, and a weight of fuel metered sensor.

8. The aeronautic engine according to claim 1 , wherein the insulating material of the housing comprises composite material comprising a fibrous reinforcement densified by a polymer matrix.

Assignees

• Snecma

Inventors

• Sayn-Urpar Julien
• Fert Jeremy Edmond
• Kohn Thierry
• Pavillet Julien

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F01D25/28 Primary

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

• B64D31/00 Primary

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• H01R4/64

  Connections between or with conductive parts having primarily a non-electric function, e.g. frame, casing, rail · CPC title