초록 ▼

The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC

The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M1) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (M1 and M2) controlled respectively by first and second control means (MC1 and MC2). The device is remarkable in that it comprises check means (C) provided with main means (C1), the main means (C1) controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f) as determined in accordance with the method of the invention.

대표청구항 ▼

What is claimed is: 1. A method of performing a health check on at least a first turbine engine (M1) of a rotorcraft, said rotorcraft having first and second turbine engines (M1 and M2) presenting, before said health check, respectively first and second normal values (V1c, V2c) for a surveillance p

What is claimed is: 1. A method of performing a health check on at least a first turbine engine (M1) of a rotorcraft, said rotorcraft having first and second turbine engines (M1 and M2) presenting, before said health check, respectively first and second normal values (V1c, V2c) for a surveillance parameter and also real first and second final values (V1f, V2f) for said surveillance parameter during said health check, wherein the following steps are performed in succession: a) determining the real first final value (V1f) of said surveillance parameter that said first turbine engine (M1) is to reach in order to perform said health check accurately; b) assuming that said real second final value (V2f) of said surveillance parameter of said second turbine engine (M2) is equal to said second normal value (V2c) of said second turbine engine (M2); c) determining the difference between said real first final value (V1f) and said real second final value (V2f); d) if said difference is greater than a predetermined threshold, readjusting said real second final value (V2f) so that the difference between said real first final value (V1f) and said real second final value (V2f) is less than said predetermined threshold during the health check; and e) controlling said first turbine engine (M1) so that said first normal value (V1c) before said health check reaches said real first final value (V1f) during said health check, and controlling said second turbine engine (M2) so that said second normal value (V2c) before said health check reaches said real second final value (V2f). 2. A method according to claim 1, wherein, for said first turbine engine (M1) being provided with a gas generator, and said surveillance parameter being the speed of rotation (Ng) of said gas generator, during the step a), the real first final value (V1f) of said surveillance parameter is determined by modulating a given reduced final value with the help of the external temperature (T0) of the surroundings of said rotorcraft. 3. A method according to claim 1, wherein, for said surveillance parameter being the power developed by said turbine engine, during step a), the real first final value (V1f) of said surveillance parameter is determined by modulating a given reduced final value with the help of the external pressure (P0) and the temperature (T0) of the surroundings of said rotorcraft. 4. A method according to claim 1, wherein, for said rotorcraft being provided with a power transmission gearbox having two inlets connected respectively to the first and second turbine engines (M1 and M2), each inlet being suitable for accepting a maximum power, during a step a′) that follows step a), the following steps are performed in succession: a′1) determining an intermediate power that said first turbine engine (M1) is to deliver so that said surveillance parameter reaches said real first final value (V1f); and a′2) if said intermediate power is less than the maximum power accepted by said power transmission gearbox, then said real first final value (V1f) remains unchanged; or else a′3) if said intermediate power is greater than said maximum power accepted by said power transmission gearbox, then said real first final value (V1f) is made equal to the value that the surveillance parameter needs to reach in order to cause said final first power of said first turbine engine (M1) to be equal to said maximum power. 5. A method according to claim 4, wherein, during step a′), account is taken of engine mounting losses. 6. A method according to claim 1, wherein, prior to step c), said first and second turbine engines (M1 and M2) together develop a total power, and said real second final value (V2f) is readjusted during step b) in such a manner that the total power developed before said health check is equal to the total power developed during said health check. 7. A device for implementing a health check on at least one turbine engine (M1) of a twin-engined rotorcraft, said rotorcraft being provided with first and second turbine engines (M1 and M2) respectively controlled by first and second control means (MC1 and MC2), the device comprising check means (C) provided with main means (C1) for successively: determining the real first final value (V1f) of a surveillance parameter of the first turbine engine (M1) that needs to be reached in order to perform the health check of said first turbine engine (M1) accurately; assuming that the real second final value (V2f) of the surveillance parameter of the second turbine engine (M2) is equal to the second normal value (V2c) of said second turbine engine (M2); determining the difference between the real first final value (V1f) and the second final value (V2f); if the difference is greater than a predetermined threshold, readjusting said second final value (V2f) so that said difference becomes less than said threshold; and controlling the first and second control means (MC1 and MC2) so that the surveillance parameters of the first and second turbine engines (M1 and M2) respectively reach the real first and second final values (V1f and V2f). 8. A device according to claim 7, including secondary means (C2) that receive a plurality of items of information for performing the health check and for establishing a diagnosis of the health of said first and second turbine engines (M1 and M2). 9. A device according to claim 8, wherein said secondary means (C2) is integrated in said check means (C). 10. A device according to claim 8, wherein each control means (MC1, MC2) includes secondary means (C2). 11. A device according to claim 8, wherein said information items come from main sensors (1) measuring the values of parameters of said first turbine engine (M1). 12. A device according to claim 8, wherein said secondary means (C2) integrates the effects of engine mounting that might modify a parameter of a turbine engine mounted on a rotorcraft as compared with the same turbine engine mounted on a test bench. 13. A device according to claim 7, wherein said main means (C1) integrate the effects of engine mounting that might modify a parameter of a turbine engine mounted on a rotorcraft compared with the same turbine engine mounted on a test bench. 14. A device according to claim 7, wherein the main means (C1) determines automatically the real first final value (V1f) that a surveillance parameter of said first turbine engine needs to reach in order to ensure that the health check is performed accurately. 15. A device according to claim 7, wherein said device includes an interface to enable the pilot of said rotorcraft to specify to the main means (C) the real first final value (V1f) that a surveillance parameter of said first turbine engine (M1) is to reach so that the health check is performed accurately. 16. A device according to claim 7, wherein the real first final value (V1f) that a surveillance parameter of said first turbine engine (M1) is to reach in order to ensure that the health check is performed accurately is determined with the help of a reduced final value modulated by at least the external pressure surrounding said rotorcraft, an interface enabling the pilot of said rotorcraft to specify the reduced final value to the main means (C) so that said main means (C) determine said real first final value (V1f) to be reached by said surveillance parameter of said first turbine engine (M1).