Patent attributes
An aircraft turbomachine (10) comprising a gas generator (12) and a fan (14) located upstream of the gas generator and surrounded by a fan casing (16), the gas generator comprising a high-pressure body (12b) and a low-pressure body (12a) which is connected to a shaft of the fan (32), the high- and low-pressure bodies comprising compressors (22, 20) between which is located an intermediate casing (40) which connects the gas generator to said fan casing, the turbomachine further comprising first decoupling means (60) configured to disconnect the fan shaft from the low-pressure body, following a detection of a critical event, characterised in that it comprises second decoupling means configured to disconnect a blades stator from the compressor of the low-pressure body opposite the intermediate casing, these second fixing means comprising fusible means (62) for fixing the bladed stator to the intermediate casing.
