Insulating Test Engine Hood for a Turbine Engine on a Test Bench

Patent metadata

Field	Value
Publication number	US-2016108753-A1
Application number	US-201514867973-A
Country	US
Kind code	A1
Filing date	Sep 28, 2015
Priority date	Oct 15, 2014
Publication date	Apr 21, 2016
Grant date	—

Abstract

The present application concerns a test engine hood for a turbine engine, such as a double flow turbine. The test hood allows replacement of a flight engine hood during tests on a test bench on the ground where the temperature conditions could damage the flight hood. The test hood includes a tubular wall of carbon-fibre epoxy composite, and metal flanges upstream and downstream. To provide thermal protection, the test hood includes a layer of silicone with a majority of polysiloxane. The layer covers the entire inner surface of the wall to create a barrier. The present application also concerns a method for testing a turbine engine on a test bench, where the turbine engine is fitted with a test casing. The present application also concerns a use of silicone for thermal insulation of the inside of the test hood of the turbine engine on a test bench on the ground.

First claim

We claim:

1 . A test engine hood for a turbine engine, the test engine hood including an annular duct for an annular flow, and being configured to replace a flight engine hood of the turbine engine during a test of the turbine engine on a test bench, the test engine hood comprising:
a wall with an outer surface configured to delimit inwardly the annular flow of the turbine engine; an inner surface opposite the outer surface; and a silicone layer covering the inner surface of the wall and insulating the wall thermally.

2 . The test engine hood in accordance with claim 1 , wherein the silicone layer is electrically insulating.

3 . The test engine hood in accordance with claim 1 , wherein the wall is made of composite material with an organic matrix.

4 . The test engine hood in accordance with claim 3 , wherein the composite material comprises:
carbon fibres and glass fibres, and where applicable, a stratified preform with a stack of fibrous layers with glass-fibre layers and carbon-fibre layers.

5 . The test engine hood in accordance with claim 1 , wherein the silicone layer covers the majority of the wall's inner surface.

6 . The test engine hood in accordance with claim 1 , wherein the wall is arcuate and is formed by two half-shells defining a casing, the casing comprising:
attached axial fixing flanges joining the half-shells.

7 . The test engine hood in accordance with claim 1 , further comprising:
electrical connections passing through the wall, the electrical connections being electrically connected to sensors, and where applicable, the electrical connections extend between the wall and the silicone layer.

8 . The test engine hood in accordance with claim 1 , further comprising:
electrical connections passing radially through the silicone layer.

9 . The test engine hood in accordance with claim 1 , further comprising:
sensors which are in contact with the silicone layer.

10 . The test engine hood in accordance with claim 1 , further comprising:
an arcuate flange at an axial end of the wall, the arcuate flange contacting the silicone layer.

11 . The test engine hood in accordance with claim 1 , further comprising:
an arcuate flange which is made of metal and which is fixed to the wall via fixing pins extending radially towards the inside.

12 . The test engine hood in accordance with claim 1 , further comprising:
an arcuate flange comprising:
a first arcuate portion which follows the inner surface of the wall; and
a second arcuate portion which extends along the wall flush with the outer surface of the wall, so as to guide the annular flow of the turbine engine.

13 . The test engine hood in accordance with claim 1 , wherein the silicone layer has a thickness between 1.00 mm and 10.00 mm.

14 . A test engine hood for a turbine engine exhibiting an annular duct for an annular flow, the test engine hood being configured to replace a flight engine hood of the turbine engine during a test of the turbine engine on a test bench, the test hood comprising:
a wall with an outer surface configured to delimit inwardly the annular flow of the turbine engine; an inner surface opposite the outer surface; and a silicone layer covering the inner surface of the wall and insulating the wall thermally, the silicone layer comprising:
at least 30% by mass of polysiloxane in contact with the inner surface.

15 . The test engine hood in accordance with claim 14 , wherein the silicone layer comprises:
less than 20% by mass of quartz particles, the quartz particles being in contact with the wall's inner surface.

16 . The test engine hood in accordance with claim 14 , wherein the silicone layer comprises:
reticulants.

17 . A method for testing a turbine engine on a test bench, the method comprising:
(b) mounting a test engine hood on the turbine engine, the test engine hood comprising:
a wall with an inner surface surrounding the turbine engine;
(c) fixing the turbine engine to the test bench; and (d) testing the turbine engine on the test bench; wherein the test engine hood comprises:
a silicone layer covering the inner surface of the wall and insulating the wall thermally.

18 . The method in accordance with claim 17 , wherein during step (c), the test engine hood is fixed to the test bench, the test bench comprising:
an adapter with fixing portions which cooperate with the test hood.

19 . The method in accordance with claim 17 , wherein the test hood comprises:
an arcuate flange at each upstream and downstream axial end of the wall; wherein, during step (b), each flange comes into arcuate contact with the turbine engine.

20 . The method in accordance with claim 17 , wherein during step (b), the silicone layer surrounds the turbine engine over the majority of the axial length of the wall.

Assignees

• Techspace Aero Sa

Inventors

• Tran Quac Hung
• Croes Pierre
• Noelmans Aurore

Classifications

• C09D183/04 Primary

  Polysiloxanes · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title

• F01D25/285

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F05D2300/30

  Inorganic materials other than provided for in groups F05D2300/10 - F05D2300/2291 · CPC title