System and method for starting the engines of a twin-engine aircraft

Patent metadata

Field	Value
Publication number	US-10494115-B2
Application number	US-201715434284-A
Country	US
Kind code	B2
Filing date	Feb 16, 2017
Priority date	Feb 16, 2016
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.

First claim

The invention claimed is:

1. A method for the automatic starting of a twin-engine aircraft, the aircraft comprising a first and a second engine each having a high-pressure stage comprising at least one rotor, the starting method comprising the automatic starting of a first and then of a second engine, the starting of the first engine comprising implementing a starting cycle that takes place in four successive phases, these being:
a starting phase in which at least one rotor of the high-pressure stage of the first engine is spun up via a compressed-air-generating source;
a holding phase in which the rotational speed of the at least one rotor of the first engine is held at a speed that is substantially constant and less than a nominal value for a predetermined duration;
an ignition phase in which combustion of an air-fuel mixture is initiated in the first engine; and
a run-up phase in which the rotational speed of the at least one rotor of the first engine is increased until it reaches the nominal value,
the method being one wherein, concomitantly with the starting cycle for the first engine, comprises the steps of:
spinning up at least one rotor of the high-pressure stage of the second engine for a predetermined duration, using the compressed-air-generating source, to a speed that is substantially constant and less than the nominal value, and
wherein, once the run-up phase of the starting cycle for the first engine is complete, the second engine is started, the starting of the second engine comprises
implementing a starting cycle that takes place in three successive phases, these being:
a starting phase in which at least one rotor of the high-pressure stage of the second engine is spun up via a compressed-air-generating source;
an ignition phase in which combustion of an air-fuel mixture is initiated in the second engine; and
a run-up phase in which the rotational speed of the at least one rotor of the second engine is increased until it reaches the nominal value.

2. The method for the automatic starting of a twin-engine aircraft as claimed in claim 1 , wherein the ignition phase of the starting cycle for the first engine is implemented following expiry of the duration during which the at least one rotor of the high-pressure stage of the second engine is spun up to a speed that is substantially constant and less than the nominal value.

3. A system for starting the engines of a twin-engine aircraft configured to implement the method for the automatic starting of a twin-engine aircraft as claimed in claim 1 , the aircraft having a first and a second engine each having a high-pressure stage comprising at least one rotor, and a compressed-air-generating source for spinning up the at least one rotor of each of said engine systems, the starting system further comprising:
a first and a second engine system respectively associated with the first and with the second engine,
each engine system comprising an engine control unit connected to the engine and configured to control said engine, and

an interface unit connected to said control unit and connected to said source,
wherein the two engine systems are connected to one another.

4. The starting system as claimed in claim 3 , wherein a signal transmitted by the first engine system to the second engine system comprises a bit indicative of activation of a holding phase during which the rotational speed of the at least one rotor of the first engine is held at a speed that is substantially constant and less than a nominal value for a predetermined duration, and wherein a signal transmitted by the second engine system to the first engine system comprises a bit indicative of activation of a holding phase during which the rotational speed of the at least one rotor of the second engine is held at a speed that is substantially constant and less than the nominal value for a predetermined duration.

5. The starting system as claimed in claim 3 , wherein a signal transmitted by an interface unit of an engine system associated with an engine to the control unit of said engine system comprises a bit indicative of the activation of a starting cycle that takes place in three successive phases, these being:
a starting phase in which at least one rotor of the high-pressure stage of the engine is spun up via a compressed-air-generating source;
an ignition phase in which combustion of an air-fuel mixture is initiated in the engine; and
a run-up phase in which the rotational speed of the at least one rotor of the engine is increased until it reaches the nominal value.

6. The starting system as claimed in claim 3 , wherein the control unit of the first engine system is connected to the control unit of the second engine system.

7. The starting system as claimed in claim 3 , wherein the interface unit of the first engine system is connected to the interface unit of the second engine system.

Assignees

• Airbus Operations Sas
• Airbus Sas

Inventors

• Zaccaria Patrick
• Brousse Pierre-Henri
• Manneville Alexis
• Roux Paul-Emile
• Lozach Damien
• Molliet Christine

Classifications

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title

• F05D2260/85

  Starting · CPC title

• F05D2240/20

  Rotors · CPC title

• F05D2240/40

  Use of a multiplicity of similar components · CPC title