Abstract: 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.

Abstract: Method for establishing a sizing specification for an equipment intended to be mounted on a turbomachine structure such as a casing, the method comprising the following steps: selecting (S8) an incident likely to occur on the structure, such as the loss of a rotor element of the turbomachine; simulating (S14) the presence of the equipment on the structure, at an attachment point, by means of a mechanical oscillator having at least a natural frequency (f0) and at least a damping rate (?); varying the natural frequency and/or damping rate according to at least two values; determining (S18) a sizing acceleration for the mechanical oscillator in response to the incident for each of said values of the natural frequency and damping rate; delivering (S20) the specification comprising the sizing accelerations and the corresponding natural frequency and damping rate values.

Abstract: 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.

Abstract: A fan disk is for a jet engine in which there flows a gas stream in a flow direction. A pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.

Abstract: The invention relates to a method for measuring the kinematics of at least one rotor of an engine (14), especially a turbomachine, characterized in that the measurement is performed by gamma ray scintigraphy, the method comprising steps consisting in providing the rotor with radioactive tracers, and, during the operation of the engine, detecting the gamma rays emitted by said tracers by means of at least two gamma cameras (30).

Abstract: The invention relates to a method for measuring the kinematics of at least one rotor of an engine (14), especially a turbomachine, characterised in that the measurement is performed by gamma ray scintigraphy, the method comprising steps consisting in providing the rotor with radioactive tracers, and, during the operation of the engine, detecting the gamma rays emitted by said tracers by means of at least two gamma cameras (30).

Abstract: A fan disk is for a jet engine in which there flows a gas stream in a flow direction, pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.