Abstract: A power plant (10) having a first and second turboshaft engines (11, 16) and an emergency system (20) for injecting fluid into said engines (11, 16). First and second pressurization pipes (26, 28) connect a tank (21) to each gas generator of the engines. In addition, the system (20) includes an injector device (35, 40) for each engine, which device comprises an injector pipe (36, 41) connecting said tank (21) to at least one injector nozzle (31). A distributor (51, 52) is arranged on each injector pipe (36, 41), each valve (51) feeding one of the engines while being connected to the gas generator of the other engine.

Abstract: A method of managing a power plant for a rotary wing aircraft, said power plant comprising two main engines, a secondary engine, and a main power transmission gearbox (MGB). Said main and secondary engines mechanically driving said MGB so as to rotate a main rotor of said aircraft. Said secondary engine delivers two distinct mechanical power levels so that said main and secondary engines together deliver sufficient mechanical power to enable said aircraft to fly, firstly a first secondary mechanical power MPS1 and secondly a second secondary mechanical power MPS2 suitable for compensating for a loss of main mechanical power from at least one main engine.

Abstract: The fastener fitting (40) has a first fastener zone (42) for fastening to an element (24) of the deployment mechanism. This fastener fitting (40) has two longitudinal arms (46A, 46B) that extend substantially in parallel and in the same direction from the first fastener zone (42). The free ends of these arms that are remote from the first fastener zone are separate, with each arm being provided with a distinct fastener surface (48A, 48B), these respective fastener surfaces together forming the second fastener zone.

Abstract: A method of managing a power plant for a rotary wing aircraft, said power plant comprising two main engines, a secondary engine, and a main power transmission gearbox (MGB). Said main and secondary engines mechanically driving said MGB so as to rotate a main rotor of said aircraft. Said secondary engine delivers two distinct mechanical power levels so that said main and secondary engines together deliver sufficient mechanical power to enable said aircraft to fly, firstly a first secondary mechanical power MPS1 and secondly a second secondary mechanical power MPS2 suitable for compensating for a loss of main mechanical power from at least one main engine.

Abstract: A power plant (10) having a first and second turboshaft engines (11, 16) and an emergency system (20) for injecting fluid into said engines (11, 16). First and second pressurization pipes (26, 28) connect a tank (21) to each gas generator of the engines. In addition, the system (20) includes an injector device (35, 40) for each engine, which device comprises an injector pipe (36, 41) connecting said tank (21) to at least one injector nozzle (31). A distributor (51, 52) is arranged on each injector pipe (36, 41), each valve (51) feeding one of the engines while being connected to the gas generator of the other engine.

Abstract: The present invention relates to a deployable diverging bell (2) for a thruster, the bell comprising: a stationary first diverging bell portion (3) suitable for being connected to a stationary support of the thruster (1); a movable second diverging bell portion (4) that is movable between a retracted position and a deployed position in which it is connected to the downstream end of the first diverging bell portion (3) in order to extend it (3); and at least one deployment mechanism (6, 8) including means (6) for moving the movable second diverging bell portion (4) relative to the stationary first diverging bell portion (3) in order to deploy the movable second diverging bell portion (4) from its retracted position to its deployed position; the bell being characterized in that it includes at least one damper means (13) for damping vibration coming from the movable second diverging bell portion (4) and/or the deployment mechanism (6, 8).

Abstract: A test bench for a reaction engine including a nozzle having a divergent. The bench includes a mechanism for holding the divergent in position, capable of holding the divergent so that its axis is vertical, and capable of interacting with a downstream portion of the divergent located in the downstream half thereof to limit distortion and/or displacement of this downstream portion. The test bench enables the divergent to remain undamaged even if lateral forces are applied to it during testing.

Abstract: The present invention relates to a deployable diverging bell (2) for a thruster, the bell comprising: a stationary first diverging bell portion (3) suitable for being connected to a stationary support of the thruster (1); a movable second diverging bell portion (4) that is movable between a retracted position and a deployed position in which it is connected to the downstream end of the first diverging bell portion (3) in order to extend it (3); and at least one deployment mechanism (6, 8) including means (6) for moving the movable second diverging bell portion (4) relative to the stationary first diverging bell portion (3) in order to deploy the movable second diverging bell portion (4) from its retracted position to its deployed position; the bell being characterized in that it includes at least one damper means (13) for damping vibration coming from the movable second diverging bell portion (4) and/or the deployment mechanism (6, 8).

Abstract: The fastener fitting (40) has a first fastener zone (42) for fastening to an element (24) of the deployment mechanism. This fastener fitting (40) has two longitudinal arms (46A, 46B) that extend substantially in parallel and in the same direction from the first fastener zone (42). The free ends of these arms that are remote from the first fastener zone are separate, with each arm being provided with a distinct fastener surface (48A, 48B), these respective fastener surfaces together forming the second fastener zone.