초록 ▼

In order to regulate a power plant (105) having a gas generator (1) and a free turbine (3) to drive a rotary wing, a first speed of rotation (NTL) of the free turbine (3) is regulated on a first setpoint value (NTL*) equal either to a regulation term (NRc) or to a predetermined setpoint threshold (N

In order to regulate a power plant (105) having a gas generator (1) and a free turbine (3) to drive a rotary wing, a first speed of rotation (NTL) of the free turbine (3) is regulated on a first setpoint value (NTL*) equal either to a regulation term (NRc) or to a predetermined setpoint threshold (NTL*). The regulation term (NRc) is a function of a third speed of rotation (NR) of said rotary wing in accordance, where NRc=NR*(1−d), “d” representing a non-zero constant lying in the range 0 to 1.

대표청구항 ▼

1. A method of regulating a power plant having a gas generator and a free turbine in a rotary wing aircraft, the method comprising: using a measured value of a first speed of rotation (NTL) of the free turbine to cause the first speed of rotation (NTL) to tend towards a first setpoint value (NTL*) b

1. A method of regulating a power plant having a gas generator and a free turbine in a rotary wing aircraft, the method comprising: using a measured value of a first speed of rotation (NTL) of the free turbine to cause the first speed of rotation (NTL) to tend towards a first setpoint value (NTL*) by controlling a second speed of rotation (NG) of said gas generator by a second setpoint value (NG*);monitoring variation in a collective pitch of blades of the rotary wing and, as a function of said variation, temporarily anticipating a power demand of the rotary wing by correcting the second setpoint value (NG*);reading a current value of a third speed of rotation (NR) of the rotary wing to calculate a regulation term (NRc) that is a function of the third speed of rotation (NR) by using the following relationship: NRc=NR*(1−d)where “NRc” represents said regulation term, “NR” represents said third speed of rotation, and “d” represents a non-zero constant lying in the range 0 to 1;comparing the values of the regulation term (NRc) with a predetermined setpoint threshold (NTL′) of the first speed of rotation (NTL) of the free turbine; andregulating the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) equal either to said regulation term (NRc) or to said setpoint threshold (NTL′), as a function of predetermined conditions. 2. A method according to claim 1, wherein the method compare the values of the regulation term (NRc) with the setpoint threshold (NTL′) provides for using a constant (d) lying in the range 0.005 to 0.1. 3. A method according to claim 2, wherein the method provides for using a constant (d) equal to 0.01. 4. A method according to claim 1, wherein the first speed of rotation (NTL) of the free turbine is regulated on a first setpoint value (NTL*) equal to said regulation term (NRc) when the regulation term (NRc) is greater than said setpoint threshold (NTL′), and the first speed of rotation (NTL) is regulated on a first setpoint value (NTL*) equal to said setpoint threshold (NTL′) when the setpoint threshold is greater than said regulation term (NRc). 5. A regulation method according to claim 1, wherein if the third speed of rotation (NR) of the rotary wing is less than the sum of the first speed of rotation (NTL) of the free turbine plus a first predetermined invariant, and if the time derivative of the third speed of rotation (NR) is greater than a second invariant, then the first speed of rotation (NTL) is regulated on a first setpoint value (NTL*) equal to said regulation term (NRc), otherwise the first speed of rotation (NTL) is regulated on a first setpoint value (NTL*) equal to the setpoint threshold (NTL′). 6. A method according to claim 1, wherein the second setpoint value (NG*) is determined by proportional integral regulation. 7. A method according to claim 1, wherein the method provides for using a computer of the power plant to implement its constituent steps. 8. A method according to claim 1, wherein the method provides for using a computer of the avionics system of the aircraft. 9. A method according to claim 1, wherein the power plant is connected to the rotary wing via a main gearbox (MGB) and a free-wheel mechanism. 10. A regulator device for regulating a power plant of a rotary wing aircraft, the power plant being provided with a gas generator and a free turbine, said regulator device comprising a computer provided with a processor and a memory containing instructions, the instructions enabling the processor to perform the following operations: using a measured value of a first speed of rotation (NTL) of the free turbine to cause the first speed of rotation (NTL) to tend towards a first setpoint value (NTL*) by controlling a second speed of rotation (NG) of the gas generator by a second setpoint value (NG*);determining how much a collective pitch of blades of the rotary wing is varying, and as a function of said variation, temporarily anticipating a power demand of the rotary wing by correcting the second setpoint value (NG*);determining a current value of a third speed of rotation (NR) of the rotary wing;calculating a regulation term (NRc) that is a function of the third speed of rotation (NR) by using the following relationship: NRc=NR*(1−d)where “NRc” represents said regulation term, “NR” represents said third speed of rotation, and “d” represents a non-zero constant lying in the range 0 to 1;comparing the values of said regulation term (NRc) and of a predetermined setpoint threshold (NTL′) of the first speed of rotation (NTL) of the free turbine; andregulating the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) that is equal either to said regulation term (NRc) or else to said setpoint threshold (NTL′), as a function of predetermined conditions. 11. An aircraft comprising: a rotary wing having a rotor and a plurality of blades;an engine configured to drive the rotor, the engine having a gas generator and a free turbine; anda controller for regulating the engine, the controller configured to: use a measured value of a first speed of rotation (NTL) of the free turbine to cause the first speed of rotation (NTL) to tend towards a first setpoint value (NTL*) by controlling a second speed of rotation (NG) of the gas generator by a second setpoint value (NG*);monitor variation in a collective pitch of the blades of the rotary wing and, as a function of the variation, temporarily anticipating a power demand of the rotary wing by correcting the second setpoint value (NG*);read a current value of a third speed of rotation (NR) of the rotor to calculate a regulation term (NRc) that is a function of the third speed of rotation (NR) by using the following relationship: NRc=NR*(1−d)where “NRc” represents said regulation term, “NR” represents said third speed of rotation, and “d” represents a non-zero constant lying in the range 0 to 1; andregulate the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) equal either to the regulation term (NRc) or to a predetermined setpoint threshold (NTL′) of the first speed of rotation (NTL) of the free turbine, as a function of predetermined conditions. 12. The aircraft of claim 11 wherein: the controller is further configured to compare the values of the regulation term (NRc) with the setpoint threshold (NTL′) and to regulate the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) equal to the regulation term (NRc) when the regulation term (NRc) is greater than the setpoint threshold (NTL′). 13. The aircraft of claim 11 wherein: the controller is further configured to compare the values of the regulation term (NRc) with the setpoint threshold (NTL′) and to regulate the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) equal to the setpoint threshold (NTL′) when the setpoint threshold is greater than the regulation term (NRc). 14. The aircraft of claim 11 wherein: the controller is further configured to regulate the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) equal to the regulation term (NRc) if the third speed of rotation (NR) of the rotor is less than the sum of the first speed of rotation (NTL) plus a first predetermined invariant and if the time derivative of the third speed of rotation (NR) is greater than a second invariant. 15. The aircraft of claim 14 wherein: the controller is further configured to regulate the first speed of rotation (NTL) of the free turbine on a first setpoint value (NTL*) equal to the setpoint threshold (NTL′) if either the third speed of rotation (NR) of the rotor is greater than the sum of the first speed of rotation (NTL) plus a first predetermined invariant or if the time derivative of the third speed of rotation (NR) is less than a second invariant.