FIELD: engines and pumps.
SUBSTANCE: invention relates to methods of controlling specific fuel consumption of a helicopter equipped with two gas turbine engines. Each of engines (1, 2) comprises gas generator (11, 21), equipped with combustion chamber (CC). At least one of gas turbine engines (1, 2) is configured for independent operation in prolonged flight mode (B, E, C). Other engine (2, 1) is in idle mode with zero power, which is selected from a mode of maintaining engine (1, 2) in rotation on combustion chamber (CC), mode of maintaining engine (1, 2) during rotation with switched off combustion chamber (CC) and mode for zero rotation of engine (1, 2) with switched off combustion chamber (CC). Engine (2, 1) is configured to switch to acceleration mode of gas generator of said engine (2, 1) by means of drive (E1, E2) which is compatible with emergency re-start at emergency outlet, and said emergency restart carried out, in case of at least one failed preliminary normal attempt of restart (U0). In case of failure of gas turbine engine (1, 2), gas turbine engine (2, 1), is started again by emergency assistance (U2, U1). Control system (4) comprises drive means (E1, E2) and device (U1, U2) for emergency assistance of gas generators (11, 21) depending on conditions and phases of helicopter flight control in accordance with conditions of flight task, pre-recorded in memory device (6) of said system (4).
EFFECT: reduced specific consumption of Cs twin-engine helicopter with preservation of minimum power safety conditions, provided for any type of flight.
12 cl, 3 dwg
