| 简介 |
The combustion chamber wall for aeronautical motors, comprises a composite material substrate (10) with ceramic matrix containing silicon and a barrier environment formed on the substrate, an exterior layer (12) for anti-corrosion protection having an aluminosilicate compound of alkaline or alkaline-earth or rare earth element, and a silicon adhesion underlayer (14) formed between the substrate and the anti-corrosion protection layer. The adhesion underlayer with evolutionary composition of external face side ends by a pure mullite thin layer (14a). The combustion chamber wall for aeronautical motors, comprises a composite material substrate (10) with ceramic matrix containing silicon and a barrier environment formed on the substrate, an exterior layer (12) for anti-corrosion protection having an aluminosilicate compound of alkaline or alkaline-earth or rare earth element, and a silicon adhesion underlayer (14) formed between the substrate and the anti-corrosion protection layer. The adhesion underlayer with evolutionary composition of external face side ends by a pure mullite thin layer (14a), and evolutionary composition of internal face side starts by a silicon thin layer formed on the substrate. The silicon and pure mullite layer have a thickness of 50 mu m. The barrier environment comprises an external layer (16) for thermal protection formed on the anti corrosion layer, an additional anti corrosion protection layer formed by the aluminosilicate compound, an underlying layer formed above the adhesion underlayer, and an association of the compound with the mullite. The underlying layer evolves between the pure mullite with an internal face situated on the side of the adhesion underlayer and compound forming the anti-corrosion protection layer with an external face situated on the side, with progressive decrease in the mullite content and progressive increase in the compound content. |
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