Method of automatically regulating aircraft power plant gas generator and free turbine speeds as a function of heating, electricity generation, noise emission, and fuel consumption

Patent metadata

Field	Value
Publication number	US-9476360-B2
Application number	US-201313753690-A
Country	US
Kind code	B2
Filing date	Jan 30, 2013
Priority date	Feb 7, 2012
Publication date	Oct 25, 2016
Grant date	Oct 25, 2016

Abstract

The present invention relates to an automatic method of regulating a power plant ( 3 ′) of an aircraft ( 1 ), the power plant having at least one turbine engine ( 3 ), each engine ( 3 ) being capable of operating in an idling mode of operation. A calculation system ( 15 ) executes stored instructions in order to implement the idling mode of operation as a function of operational and ordered conditions either via a first regulation mode by regulating a first speed of rotation (Ng) of said gas generator ( 4 ), or via a second mode of regulation by regulating a second speed of rotation (NTL) of said free turbine ( 7 ).

First claim

What is claimed is:

1. A method of automatically regulating a power plant of an aircraft having a turbine engine, the engine being operable in an idling mode of operation and having a gas generator and a free turbine, the method comprising:
during a selection step (STPO); selecting that the engine be operated in the idling mode of operation;
during a regulation step (STP 1 ), while the engine is selected to be operated in the idling mode of operation and the aircraft is standing on the ground, implementing the idling mode of operation and operating the engine in compliance with the idling mode of operation;
wherein operating the engine in compliance with the idling mode of operation during the regulation step (STP 1 ) includes automatically regulating either a first speed of rotation (Ng) of the gas generator of the engine through a second mode of regulation depending on operational and hierarchically ordered conditions; and
during the regulation step (STP 1 ) while the idling mode of operation is implemented, determining an original gas generator speed of rotation level (Ng 1 ) that is to be reached by the gas generator for regulating the speed of rotation (NTL) of the free turbine at a critical free turbine speed of rotation level (NTLcrit) defined by a manufacturer in order to satisfy a first one of the operational and hierarchical ordered conditions;
determining an electricity generation target (ITOT) that the power plant is to deliver in order to satisfy a second one of the operational and hierarchically ordered conditions; and
when the power plant cannot deliver the electricity generation target while the gas generator is operating at the first original gas generator speed of rotation level (Ng 1 ), operating the engine in compliance with the idling mode of operation by automatically regulating the speed of rotation (Ng) of the gas generator.

2. The method according to claim 1 , further comprising selecting the operational and hierarchically ordered conditions from a list of operational conditions, the list of operational conditions including:
generation of hot air from the engine for heating the aircraft as a function of outside conditions;
generation of electricity from the gas generator for electrically powering the aircraft;
minimization of noise emission; and
minimization of fuel consumption.

3. The method according to claim 2 , further comprising establishing the hierarchical order of the operational and hierarchically ordered conditions as a function of needs defined by an operator of the aircraft.

4. The method according to claim 1 , wherein the operational and hierarchically ordered conditions include the following operational conditions in the following hierarchical order:
generation of hot air from the engine for heating the aircraft as a function of outside conditions;
generation of electricity from the gas generator for electrically powering the aircraft;
minimization of noise emission; and
minimization of fuel consumption.

5. The method according to claim 1 , wherein the critical free turbine speed of rotation level (NTLcrit) is defined to ensure that the aircraft operates outside a ground resonance range by minimizing noise emission and fuel consumption by the engine.

6. The method according to claim 1 , wherein during the regulation step (STP 1 ) while the idling mode of operation is implemented and the power plant cannot deliver the electricity generation target (ITOT) while the gas generator is operating at the original gas generator speed of rotation level (Ng 1 ), the method further comprising:
determining a setpoint hot air temperature (THOT) that is to be delivered for heating the aircraft in order to satisfy a third one of the operational and hierarchically ordered conditions;
determining a setpoint gas generator speed of rotation (Ngcons) that makes it possible to deliver the electricity generation target (ITOT);
determining whether the setpoint gas generator speed of rotation (Ngcons) makes it possible to reach the setpoint hot air temperature (THOT);
when the setpoint gas generator speed of rotation (Ngcons) makes it possible to reach the setpoint hot air temperature, operating the engine in compliance with the idling mode of operation by automatically regulating the speed of rotation (Ng) of the gas generator in order to maintain the speed of rotation (Ng) of the gas generator equal to the setpoint gas generator speed of rotation (Ngcons); and
when the setpoint gas generator speed of rotation (Ngcons) does not make it possible to reach the setpoint hot air temperature (THOT), operating the engine in compliance with the idling mode of operation by automatically regulating the speed of rotation (Ng) of the gas generator in order to maintain the speed of rotation (Ng) of the gas generator equal to a target gas generator speed of rotation that makes it possible to reach the setpoint hot air temperature (THOT).

7. The method according to claim 1 , wherein during the regulation step (STP 1 ) while the idling mode of operation is implemented and the power plant can deliver the electricity generation target (ITOT) while the gas generator is operating at the original gas generator speed of rotation level (Ng 1 ), the method further comprising:
determining a setpoint hot air temperature (THOT) that is to be delivered for heating the aircraft in order to satisfy a third one of the operational and hierarchically ordered conditions;
when the original gas generator speed of rotation level (Ng 1 ) makes it possible to reach the setpoint hot air temperature (THOT), operating the engine in compliance with the idling mode of operation by automatically regulating the speed of rotation (NTL) of the free turbine in order to maintain the speed of rotation (NTL) of the free turbine equal to the critical free turbine speed of rotation level (NTLcrit); and
when the original gas generator speed of rotation level (Ng 1 ) does not make it possible to reach the setpoint hot air temperature (THOT), determining a setpoint gas generator speed of rotation (Ngcons) that makes it possible to reach the setpoint hot air temperature (THOT) and then operating the engine in compliance with the idling mode of operation by automatically regulating the speed of rotation (Ng) of the gas generator in order to maintain the speed of rotation (Ng) of the gas generator equal to the setpoint gas generator speed of rotation (Ngcons).

8. The method according to claim 1 , further comprising inhibiting the first mode of regulation in response to a manual selection of the second mode of regulation.

9. The method according to claim 1 , further comprising implementing a stop to limit torque developed by an outlet shaft of the engine when the engine is operating in the second mode of regulation.

10. A method of automatically regulating a power plant of an aircraft having a turbine engine, the engine being operable in an idling mode of operation and having a gas generator and a free turbine, the method comprising:
during a selection step (STPO), selecting that the engine be operated in the idling mode of operation;
during a regulation step (STP 1 ), while the engine is selected to be operated in the idling mode of operation and the aircraft is standing on the ground, implementing the idling mode of operation and operating the engine in compliance with the idling mode of operation;
wherein operating the engine in compliance with the idling mode of operation during the regulation step (STP 1 ) includes automatically regulating a speed of rotation (Ng) of the gas generator of the engine through a first mode of regulation and a speed of rotation (NTL) of the free turbine of the engine through a second mode of regulation as a f

Assignees

• Airbus Helicopters

Inventors

• Corpron Alban

Classifications

• F05D2220/329

  in helicopters · CPC title

• F05D2270/02

  to control rotational speed (n) · CPC title

• B64C27/04

  Helicopters · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F05D2220/76

  an electrical generator · CPC title