Method of automatically regulating a rotorcraft power plant, a rotorcraft power plant, and a rotorcraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/12
B64D-031/00
F02C-009/28
B64C-027/04
출원번호
US-0752529
(2013-01-29)
등록번호
US-9488054
(2016-11-08)
우선권정보
FR-12 00354 (2012-02-07)
발명자
/ 주소
Corpron, Alban
출원인 / 주소
Airbus Helicopters
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
2인용 특허 :
4
초록▼
A method of automatically regulating a power plant (3′) of an aircraft (1), said power plant comprising at least one turbine engine (3), said aircraft (1) having at least one rotary wing (300) provided with a plurality of blades (301) having variable pitch and driven in rotation by said power plant
A method of automatically regulating a power plant (3′) of an aircraft (1), said power plant comprising at least one turbine engine (3), said aircraft (1) having at least one rotary wing (300) provided with a plurality of blades (301) having variable pitch and driven in rotation by said power plant (3′), it being possible for each engine (3) to operate in an idling mode of operation and in a flight mode of operation. During a selection step (STP0), a two-position selector (60) is operated either to stop each engine (3) or to set each engine (3) into operation. During a regulation step (STP1), each engine (3) is controlled automatically so as to implement the idling mode of operation if the collective pitch (CLP) of said blades is less than a threshold and if the aircraft (1) is standing on the ground.
대표청구항▼
1. A method of automatically regulating a power plant of a rotorcraft, the power plant including a turbine engine, the rotorcraft having a lift rotor including at least one rotary wing provided with a plurality of blades having variable pitch, the engine being operable in an idling mode of operation
1. A method of automatically regulating a power plant of a rotorcraft, the power plant including a turbine engine, the rotorcraft having a lift rotor including at least one rotary wing provided with a plurality of blades having variable pitch, the engine being operable in an idling mode of operation and in a flight mode of operation, the engine including a gas generator and a free turbine, the method comprising: operating a two-position selector switch either to stop the engine or to set the engine into operation;driving the at least one rotary wing in rotation by the power plant when the engine is operating;when the engine is operating, controlling the engine automatically to implement the idling mode of operation whenever (i) a collective pitch (CLP) of the blades is less than a threshold sufficient for the at least one rotary wing to generate lift for the rotorcraft to be able to take off from the ground and (ii) the rotorcraft is standing on the ground and otherwise controlling the engine automatically to implement the flight mode of operation; andwherein controlling the engine automatically to implement the idling mode of operation includes: controlling the engine automatically through a first mode of regulation by regulating a speed of rotation (Ng) of the gas generator at one time and through a second mode of regulation by regulating a speed of rotation (NTL) of the free turbine at another time;determining a target speed of rotation (Ngl) that the speed of rotation (Ng) of the gas generator is to be reach for regulating the speed of rotation (NTL) of the free turbine at a level (NTLcrit) defined by a manufacturer; andwhile the power plant cannot deliver sufficient power to satisfy an electricity generation target (ITOT) when the speed of rotation (Ng) of the gas generator is at the target speed of rotation (Ng1), regulating the speed of rotation (Ng) of the gas generator to implement the idling mode of operation. 2. The method according to claim 1, wherein: when the engine is operating, the engine is controlled automatically to implement the idling mode of operation whenever (i) the collective pitch (CLP) is less than the threshold and (ii) the rotorcraft has been standing on the ground for a delay time. 3. The method according to claim 1, wherein: the level (NTLcrit) is defined to ensure that the rotorcraft operates outside a ground resonance range. 4. The method according to claim 1, further comprising: when the power plant cannot deliver sufficient power to satisfy the electricity generation target (ITOT) and when the speed of rotation (Ng) of the gas generator is at the target speed of rotation (Ng1): determining a setpoint hot air temperature (THOT) that is to be delivered for heating the rotorcraft;determining a first setpoint speed of rotation (Ngcons) that makes it possible to deliver the electricity generation target (ITOT);determining whether the first setpoint speed of rotation (Ngcons) makes it possible to reach the setpoint hot air temperature;when the first setpoint speed of rotation (Ngcons) makes it possible to reach the setpoint hot air temperature, controlling the engine in order to maintain the first speed of rotation equal to the first setpoint speed of rotation (Ngcons);when the first setpoint speed of rotation (Ngcons) does not make it possible to reach the setpoint hot air temperature (THOT), controlling the engine in order to maintain the first speed of rotation (Ng) equal to a first target speed of rotation making it possible to reach the setpoint hot air temperature. 5. The method according to claim 1, further comprising: when the power plant can deliver sufficient power to satisfy the electricity generation target and when the speed of rotation (Ng) of the gas generator is at the target speed of rotation (Ng1): determining a setpoint hot air temperature (THOT) that is to be delivered for heating the rotorcraft;when the first original speed of rotation (Ng1) makes it possible to reach the setpoint hot air temperature (THOT), controlling the engine in order to maintain the second speed of rotation (NTL) equal to the level (NTLcrit); andwhen the first original speed of rotation (Ng1) does not make it possible to reach the setpoint hot air temperature (THOT), determining the first setpoint speed of rotation (Ngcons) making it possible to reach the setpoint hot air temperature (THOT) and controlling the engine in order to maintain the first speed of rotation (Ng) equal to the first setpoint speed of rotation (Ngcons). 6. The method according to claim 1, further comprising: inhibit means for inhibiting the first mode of regulation. 7. A power plant of a rotorcraft, the rotorcraft having a lift rotor including at least one rotary wing provided with a plurality of blades having variable pitch, the power plant comprising: a turbine engine including a gas generator and a free turbine and being operable in an idling mode of operation and in a flight mode of operation, the engine to drive the at least one rotary wing in rotation when operating; anda regulation device for regulating the power plant, the regulation device including: a first sensor for sensing a collective pitch of the blades;a second sensor for sensing whether the rotorcraft is standing on the ground;a two-position selector switch having two positions (POS1, POS2), the selector switch having a first position (POS1) requesting the engine to stop and a second position (POS2) requesting the engine to operate; anda computation system connected to the sensors and to the selector switch, the computation system, in response to the engine operating as a result of the selector switch being in the second position (POS2), executing stored instructions for automatically implementing the idling mode of operation in the engine whenever (i) a collective pitch (CLP) of the blades is less than a threshold sufficient for the at least one rotary wing to generate lift for the rotorcraft to be able to take off from the ground and (ii) the rotorcraft is standing on the ground and for otherwise automatically implementing the flight mode of operation in the engine;wherein the computation system implements the idling mode of operation in the engine by controlling the engine through a first mode of regulation by regulating a speed of rotation (Ng) of the gas generator at one time and through a second mode of regulation by regulating a speed of rotation (NTL) of the free turbine at another time;determining a target speed of rotation (Ngl) that the speed of rotation (Ng) of the gas generator is to be reach for regulating the speed of rotation (NTL) of the free turbine at a level (NTLcrit) defined by a manufacturer; andwhen the power plant cannot deliver sufficient power to satisfy an electricity generation target (ITOT) when the speed of rotation (Ng) of the gas generator is at the target speed of rotation (Ngl), regulating the speed of rotation (Ng) of the gas generator to implement the idling mode of operation. 8. The power plant according to claim 7, wherein: the computation system has an avionics computer connected to the sensors and to the selector switch and an engine computer of the engine, the engine computer being connected to the avionics computer. 9. The power plant according to claim 7, wherein the rotorcraft has an electrical network electrically powered by the power plant, wherein the regulation device further: includes a power meter for measuring the electricity consumed by the electrical network. 10. The power plant according to claim 7, wherein the regulation device further includes a third sensor for measuring the conditions of the surroundings outside the rotorcraft including at least one of an altitude of the rotorcraft, an outside pressure of the rotorcraft, and an outside temperature of the rotorcraft; andthe computation system being connected to the third sensor and executing stored instructions to determine a setpoint hot air temperature for heating the rotorcraft based on the conditions of the surroundings outside of the rotorcraft. 11. A rotorcraft comprising: a power plant including a turbine engine, the engine including a gas generator and a free turbine and being operable in an idling mode of operation and in a flight mode of operation;a lift rotor including at least one rotary wing provided with a plurality of blades having variable pitch, the at least one rotary wing to be driven in rotation by the engine when the engine operates;a two-position selector switch having a first position (POS1) requesting the engine to stop and a second position (POS2) requesting the engine to operate;a computation system;the computation system, in response to the engine operating as a result of the selector switch being in the second position (POS2), automatically implementing the idling mode of operation in the engine whenever (i) a collective pitch (CLP) of the blades is less than a threshold sufficient for the at least one rotary wing to generate lift for the rotorcraft to be able to take off from the ground and (ii) the rotorcraft is standing on the ground and otherwise automatically implementing the flight mode of operation in the engine; andwherein the computation system implements the idling mode of operation in the engine by controlling the engine through a first mode of regulation by regulating a speed of rotation (Ng) of the gas generator at one time and through a second mode of regulation by regulating a speed of rotation (NTL) of the free turbine at another time;determining a target speed of rotation (Ng1) that the speed of rotation (Ng) of the gas generator is to be reach for regulating the speed of rotation (NTL) of the free turbine at a level (NTLcrit) defined by a manufacturer; andwhen the power plant cannot deliver sufficient power to satisfy an electricity generation target (ITOT) when the speed of rotation (Ng) of the gas generator is at the target speed of rotation (Ng1), regulating the speed of rotation (Ng) of the gas generator to implement the idling mode of operation.
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