Abstract: A mode-locking laser method and system, using an external cavity for propagation of an optical field and its propagating modes; a microring resonator selected as a nested cavity to filter and resonate multiple external cavity modes and applying nonlinearity on the optical field; a gain unit, selected to amplify the optical field in the external cavity; a polarization controller, selected to control a polarization state within the system; a phase modulator selected for actively modulating phases of the nested cavity modes to achieve mode-locking; a photodetector, selected for converting optical signals into electrical signals for detection; a synthesizer, selected to generate a frequency-modulated signal for establishing a fixed phase relationship; and a tunable filter, with a bandwidth selected to select a variable number of microring resonator resonances, generating of mode-locked pulse burst trains with coexisting nanosecond and picosecond timescales and broadband comb generation with tunable central wavele

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.