Method and system for starting a turboshaft engine by cold weather

• US 8,381,509 B2
• Filed: 04/14/2008
• Issued: 02/26/2013
• Est. Priority Date: 04/23/2007
• Status: Expired due to Fees

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus Operations SAS (Airbus SE)
• Inventors: Bulin, Guillaume, Jacquet Francillon, Pierre
• Primary Examiner(s): Wongwian, Phutthiwat
• Application Number:
  US12/596,976
• Publication Number:
  US 20100107648A1
• Time in Patent Office: 1,779 Days
• Field of Search: 60/390.8, 602/66, 607/78, 607/88, 602/04, 184/6.11
• US Class Current: 60/204
• 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

A method for starting up an aircraft turbine engine using an electric starter is provided. The aircraft turbine engine is provided with at least one hydraulic fluid circuit for lubricating the aircraft turbine engine, the aircraft turbine engine lubricating circuit is provided with a temperature-regulating section that is able to remove the heat generated by the aircraft turbine engine when the aircraft turbine engine is running, the electric starter is provided with at least one hydraulic fluid circuit for lubricating parts of the electric starter, and the lubricating circuit of the electric starter is provided with the temperature-regulating section that is able to remove the heat emitted by the electric starter when the lubricating circuit of the electric starter is operating.

Claims

1. A method for starting up an aircraft turbine engine using an electric starter, said aircraft turbine engine being provided with at least one hydraulic fluid circuit for lubricating parts of said aircraft turbine engine, said hydraulic fluid circuit being provided with a temperature-regulating section that is configured to remove the heat generated by said aircraft turbine engine when said aircraft turbine engine is running, said electric starter being provided with at least one hydraulic fluid circuit for lubricating parts of said electric starter, said hydraulic fluid circuit of said electric starter being provided with a temperature-regulating section that is configured to remove the heat emitted by said electric starter when said lubricating circuit of said electric starter is operating, each of said temperature-regulating section of the hydraulic fluid circuit of the aircraft turbine engine and said temperature-regulating section of the hydraulic fluid circuit of the electric starter including at least one heat exchanger, said method comprising, when said aircraft turbine engine is being started in cold weather, the steps of:

inhibiting said temperature-regulating section of the hydraulic fluid circuit of the aircraft turbine engine;

inhibiting said temperature-regulating section of the hydraulic fluid circuit of the electric starter; and

transferring to the hydraulic fluid circuit of the aircraft turbine engine at least some of the heat energy generated in the hydraulic fluid circuit of the electric starter by said electric starter.

2. The method as claimed in claim 1, wherein heat energy is transferred from the electric starter to the hydraulic fluid of said hydraulic fluid circuit of the aircraft turbine engine when the temperature therein is at least approximately below −

20°

C.

3. The method as claimed in claim 1, wherein heat energy is transferred from the electric starter to the hydraulic fluid of the hydraulic fluid circuit of the aircraft turbine engine via said hydraulic fluid circuit of the electric starter.

4. The method as claimed in claim 3, wherein said temperature-regulating section of said hydraulic fluid circuit of said electric starter is inhibited while heat energy is being transferred from the electric starter to the hydraulic fluid of the hydraulic fluid circuit of the aircraft turbine engine.

5. The method as claimed in claim 1, wherein the transfer of heat energy from the electric starter to the hydraulic fluid of said hydraulic fluid circuit of the aircraft turbine engine is continued until the temperature of the hydraulic fluid of said hydraulic fluid circuit of the aircraft turbine engine reaches a first preset value corresponding to a viscosity of said fluid.

6. The method as claimed in claim 1, wherein the transfer of heat energy from the electric starter to the hydraulic fluid of the hydraulic fluid circuit of the aircraft turbine engine is continued until said aircraft turbine engine starts.

7. The method as claimed in claim 6, wherein the transfer of heat energy from the electric starter to the hydraulic fluid of the hydraulic fluid circuit of the aircraft turbine engine is interrupted before said aircraft turbine engine starts, if the temperature of the hydraulic fluid of the aircraft engine reaches a second preset value that carries risk of damaging said aircraft turbine engine.