Method and System for Starting a Turboshaft Engine by Cold Weather

• US 20100107648A1
• Filed: 04/14/2008
• Published: 05/06/2010
• Est. Priority Date: 04/23/2007
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Jacquet Francillon, Pierre, Bulin, Guillaume
• Granted Patent: US 8,381,509 B2
• Time in Patent Office: Days
• US Class Current: 60/778
• CPC Class Codes: F01D 19/00 Starting of machines or engines; Regulating, controlling, or safety means in connection therewith warming-up before starting F01D25/10; turning or inching gear F01D25/34
• CPC Class Codes: F01D 25/10 Heating, e.g. warming-up before starting
• CPC Class Codes: F02C 7/275 Mechanical drives
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

According to the invention, when starting a turboshaft engine (1) in cold weather, the method comprises transferring to the hydraulic fluid of the lubrication circuit (3) of the turboshaft engine (1) at least a portion of the calorific energy scattered by the electric starter (2) and inhibiting the temperature regulation means (9, 10) of said lubrication circuit (3).

Claims

1-9. -9. (canceled)

10. A method for starting up an aircraft turbine engine (1) using an electric starter (12), said turbine engine being provided with at least one hydraulic fluid circuit (3) for lubricating at least certain parts of said turbine engine (1), in which method, when said turbine engine (1) is being started in cold weather, at least some of the heat energy generated by said electric starter (12) is transferred to the hydraulic fluid of said turbine engine (1) lubricating circuit (3),

wherein with said turbine engine (1) lubricating circuit (3) being provided with temperature-regulating means (9, 10) able to remove the heat emitted by said turbine engine (1) when it is running, said temperature-regulating means (9, 10) are inhibited while heat energy is being transferred from the electric starter (12) to the hydraulic fluid of the turbine engine (1) lubricating circuit (3).

11. The method as claimed in claim 10, wherein heat energy is transferred from the electric starter (12) to the hydraulic fluid of said turbine engine (1) lubricating circuit (3) when the temperature therein is at least approximately below −

20°

C.

12. The method as claimed in claim 10, implemented using a starter (12) provided with at least one hydraulic fluid circuit (15) for lubricating at least certain parts of said starter (12), wherein heat energy is transferred from the starter (12) to the hydraulic fluid of the turbine engine (1) lubricating circuit (3) via said starter (12) lubricating circuit (15).

13. The method as claimed in claim 12, implemented using a starter (12) the lubricating circuit (15) of which is provided with temperature-regulating means (18, 19) to remove the heat emitted by said starter (12) when it is operating, wherein said temperature-regulating means (18, 19) of the starter (12) lubricating circuit (15) are inhibited while heat energy is being transferred from the electric starter (12) to the hydraulic fluid of the turbine engine (1) lubricating circuit (3).

14. The method as claimed in claim 10, wherein the transfer of heat energy from the starter (12) to the hydraulic fluid of said turbine engine (1) lubricating circuit (3) is continued until the temperature of the hydraulic fluid of said lubricating circuit (3) reaches a first preset value corresponding to a normal viscosity of said fluid.

15. The method as claimed in claim 10, wherein the transfer of heat energy from the starter (12) to the hydraulic fluid of the turbine engine (1) lubricating circuit (3) is continued until said turbine engine (1) starts.

16. The method as claimed in claim 15, wherein the transfer of heat energy from the starter (12) to the hydraulic fluid of the turbine engine (1) lubricating circuit (3) is interrupted before said turbine engine starts, if the temperature of this hydraulic fluid reaches a second preset value that carries the risk of damaging said turbine engine (1).

17. A system for starting up a turbine engine (1) using an electric starter (12), said turbine engine (1) and said starter (12) each comprising a hydraulic lubricating circuit (3, 15) provided with heat-removal temperature-regulating means (8, 9;

18, 19),

wherein it comprises;

controllable means (20, 21, 22) for the one-way transfer of heat energy between the starter (12) hydraulic lubricating circuit (15) and the turbine engine (1) lubricating hydraulic circuit (3); and

controllable means (23, 24;

26, 27) for inhibiting the temperature-regulating means (8, 9;

18, 19) of the turbine engine (1) and starter (12) lubricating hydraulic circuits (3, 15).

18. The system as claimed in claim 17, in which a part (10) of said turbine engine (1) lubricating hydraulic circuit (3) temperature-regulating means is operational when said aircraft is resting on the ground, wherein:

said starter (12) lubricating hydraulic circuit (15) does not per se comprise temperature-regulating means that are operational when the aircraft is resting on the ground; and

said controllable means (20, 21, 22) for the one-way transfer of heat energy provide a connection between said starter (12) lubricating hydraulic circuit (15) and said part (10) of the turbine engine (1) hydraulic circuit (3) temperature-regulating means so that said part (10) provides temperature regulation for said starter (12) lubricating hydraulic circuit (15) when the aircraft is resting on the ground.