| 摘要 |
The invention concerns a dual-flow turbine engine equipped with a thrust reversal system and at least one device for restricting the annular channel for the ejection of cold gases. According to the invention, each restriction device, consisting of a fitting (7) and a shutter (8) pivoting with respect to the said fitting, has sealing means disposed between the said shutter and fitting, adapted for defining at least one airtight chamber (12, 13) between these last two, each fitting (7) having, in line with each chamber, at least one orifice. Furthermore, elastic means are arranged so as to act on the shutter (8) in such a way as to produce an initial release of the latter. These devices aim to guarantee the holding of the shutter (8) in its closed position, where it is clamped against the fitting (7), during flight, whilst ensuring the opening of this shutter after landing, under the effect of the elastic means.
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