Insulating test engine hood for a turbine engine on a test bench
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-fiber 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.
1. A turbine engine comprising:
a combustion chamber; and
a test engine hood including an annular duct for an annular flow, and being intended 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 extending axially of such a length that it surrounds the combustion chamber, the test engine hood comprising:
a wall made of composite material with an organic matrix, the wall having an outer surface delimiting the annular flow and an inner surface opposite the outer surface; and
a silicone layer covering the inner surface of the wall and able to insulate the wall thermally, the silicone layer having a thickness comprised between 3.0 and 6.0 mm.
2. The turbine engine in accordance with claim 1 , wherein the silicone layer is electrically insulating.
3. The turbine engine in accordance with claim 1 , wherein the composite material comprises carbon fibres and glass fibres.
4. The turbine engine in accordance with claim 1 , wherein the silicone layer covers the majority of the inner surface of the wall.
5. The turbine engine in accordance with claim 1 , wherein the wall is arcuate and is formed by two half-shells defining a casing comprising attached axial fixing flanges joining said half-shells.
6. The turbine engine in accordance with claim 1 , further comprising electrical connections passing through the wall and through the silicone layer.
7. The turbine engine in accordance with claim 6 , further comprising sensors protruding inwardly from the silicone layer and connected to the electrical connections passing radially through the silicone layer.
8. The turbine engine in accordance with claim 1 , further comprising sensors which are in contact with the silicone layer.
9. The turbine engine in accordance with claim 1 , further comprising an arcuate flange at an axial end of the wall, said arcuate flange contacting the silicone layer.
10. The turbine engine 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 internally.
11. The turbine engine in accordance with claim 1 , further comprising an arcuate flange which comprises a first arcuate portion which extends along 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.
12. A turbine engine comprising:
a combustion chamber; and
a test engine hood, the test engine hood forming an annular duct for an annular flow, said test engine hood being intended 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 extending axially of such a length that it surrounds the combustion chamber of the turbine engine, the test engine hood comprising:
a wall made of composite material with an organic matrix, the wall having an outer surface delimiting the annular flow and an inner surface opposite the outer surface;
a silicone layer covering the inner surface of the wall and able to insulate the wall thermally, the silicone layer comprising at least 30% by mass of polysiloxane in contact with the inner surface;
electrical connections passing through the wall and through the silicone layer; and
sensors protruding inwardly from the silicone layer and connected to the electrical connections passing radially through the silicone layer.
13. The turbine engine in accordance with claim 12 , wherein the silicone layer comprises less than 20% by mass of quartz particles, the quartz particles being in contact with the inner surface of the wall.
14. The turbine engine in accordance with claim 12 , wherein the silicone layer comprises cross-linking agents.
15. The turbine engine in accordance with claim 12 , wherein at least one of the sensors is a temperature sensor or a fire detector.