Abstract: A turbopump includes a turbine fed with hot gas, a pump driven by the turbine and fed with liquid fluid, and a hot gas exhaust pipe situated downstream from the turbine. The turbopump includes a bleed-and-injection circuit including a bleeder for bleeding the liquid fluid at the outlet from the pump, a heater for heating the liquid fluid as bled off in this way so as to transform it into gaseous fluid, and an injector for injecting the gaseous fluid into an interface region of the turbopump situated between the pump and the turbine, so as to optimize the flow and temperature conditions of the fluid entering into the turbine cavity in order to eliminate the vibratory phenomena that result from interaction between the fluid and the turbine disk.

Abstract: A turbopump includes a turbine fed with hot gas, a pump driven by the turbine and fed with liquid fluid, and a hot gas exhaust pipe situated downstream from the turbine. The turbopump includes a bleed-and-injection circuit including a bleeder for bleeding the liquid fluid at the outlet from the pump, a heater for heating the liquid fluid as bled off in this way so as to transform it into gaseous fluid, and an injector for injecting the gaseous fluid into an interface region of the turbopump situated between the pump and the turbine, so as to optimize the flow and temperature conditions of the fluid entering into the turbine cavity in order to eliminate the vibratory phenomena that result from interaction between the fluid and the turbine disk.

Abstract: The invention relates to a device for damping the lateral forces due to jet separation that act on a rocket engine nozzle during a stage of starting or stopping the engine, the engine including at least two identical drive assemblies mounted on the nozzle to take up the lateral forces acting thereon, each drive assembly comprising a first member forming a strut, a second member forming an anchor structure, and an actuator. Each strut comprises means enabling it to act as a rigid strut so long as the lateral forces acting on the corresponding actuator remain below a determined force threshold, and as an element for peak limiting force and for dissipating residual kinetic energy once the forces acting on the actuator exceed the determined force threshold.

Abstract: The invention relates to a device for damping the lateral forces due to jet separation that act on a rocket engine nozzle during a stage of starting or stopping the engine, the engine including at least two identical drive assemblies mounted on the nozzle to take up the lateral forces acting thereon, each drive assembly comprising a first member forming a strut, a second member forming an anchor structure, and an actuator. Each strut comprises means enabling it to act as a rigid strut so long as the lateral forces acting on the corresponding actuator remain below a determined force threshold, and as an element for peak limiting force and for dissipating residual kinetic energy once the forces acting on the actuator exceed the determined force threshold.

Abstract: A method and system for detecting damage to the rotor of an aircraft engine using devices for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method includes the following steps: reading the acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of the acquired data; calculating a vector difference between the mean vibration vector of the determined flight and the mean vibration vector of a reference flight for the rotor speed range; comparing the modulus of the vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of the vector difference exceeds the predetermined threshold value, the steps being performed after the determined flight has been completed.

Abstract: A fan rotor includes a disk having a rim with a plurality of substantially axial grooves that are spaced apart angularly. Removable blades extend radially outwards from the periphery of the disk. Each blade has a blade root in a respective groove. A downstream flange plate can be secured to the disk with the downstream faces of the blade roots being in abutment against the downstream flange plate. An upstream flange plate is secured to the disk so as to retain the blade roots in the grooves. In the rotor, the upstream flange plate is fitted on its downstream face with a resilient device configured to exert sufficient force on the upstream faces of the blade roots, after assembly, to prevent an axial displacement of the blades during normal operation (apart from exceptional events of the type in which foreign bodies are ingested or blades are lost).

Abstract: The invention relates to a fan rotor comprising a disk having a rim with a plurality of substantially axial grooves that are regularly spaced apart angularly, a plurality of removable blades extending radially outwards from the periphery of said disk, each blade having a blade root received in a respective groove, a downstream flange plate secured to said disk with the downstream faces of the blade roots being in abutment thereagainst, and a removable upstream flange plate secured to said disk for the purpose of retaining the blade roots in the grooves. In the rotor, the upstream flange plate is fitted on its downstream face with resilient means for exerting sufficient force on the upstream faces of the blade roots, after assembly, to prevent any axial displacement of the blades during normal operation of the engine (apart from exceptional events of the type in which foreign bodies are ingested or blades are lost).

Abstract: The invention relates to detecting damage to the rotor of an aircraft engine that includes means for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method comprises the following steps: reading said acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of said acquired data; calculating a vector difference between the mean vibration vector of said determined flight and the mean vibration vector of a reference flight for said rotor speed range; comparing the modulus of said vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of said vector difference exceeds said predetermined threshold value, said steps being performed after said determined flight has been completed.