Method for synchronising the engines of an airplane with dual intermediate state

Patent metadata

Field	Value
Publication number	US-9849997-B2
Application number	US-201515304008-A
Country	US
Kind code	B2
Filing date	Apr 15, 2015
Priority date	Apr 15, 2014
Publication date	Dec 26, 2017
Grant date	Dec 26, 2017

Abstract

A method for synchronizing the engines of an airplane according to one activation logic having a deactivated state ( 20 ), an armed state ( 22 ), and one activated state ( 16 ), in which:
the switching ( 36 ) of the synchronization from the armed state to the activated state is carried out via a first and then a second successive intermediate state ( 38, 39 ) of the activation logic, every instance of the activation logic switching from the second intermediate state ( 39 ) to the activated state involves the following:
taking into consideration, on each engine, the activation state of the synchronization, and exchanging said data between the engines,
the switching of the activation logic of one of the engines to the activated state requires that the safety and activation conditions of the other engine are all met. if one of the engines enters the deactivated state, the other engine does so as well; and for each engine, the switching ( 36, 42 ) of the synchronization from the armed state to the first and then to the second intermediate state takes place automatically when a first portion and then a second portion of the safety and/or activation conditions are met.

First claim

The invention claimed is:

1. A method for synchronising there between engines of an airplane by an electronic chip encoding at least one activation logic per engine, the activation logic being intended to check the safety and/or activation conditions in order to apply the synchronisation, with each activation logic defining synchronization states of the engines, including at least a deactivated state, an armed state, and an activated state, with the method comprising, per engine:
receiving, with the electronic chip, an activation order;
when the activation order is issued by a pilot of the airplane and received with the electronic chip, switching the activation logic encoded on the electronic chip from the deactivated state to the armed state;
periodically checking, with the activation logic encoded on the electronic chip, at least one of the safety and activation conditions relative to said states, in order to define whether said conditions are met or not met,
switching the activation logic encoded on the electronic chip from the armed state to the activated state when some of the safety and/or activation conditions are met;

receiving, with the electronic chip, a deactivation order; and
when the deactivation order is issued by the pilot and received with the electronic chip or when some of said safety conditions are not met, switching the activation logic encoded on the electronic chip from the activated state or the armed state to the deactivated state,

wherein:
switching the activation logic encoded on the electronic chip from the armed state to the activated state is carried out via a first and then a second successive intermediate state of the activation logic encoded on the electronic chip,
every instance of switching the activation logic encoded on the electronic chip from the second intermediate state to the activated state involves exchanging such data between the engines carried out by an exchange digital link, so that:
switching the activation logic encoded on the electronic chip of one of the engines to the activated state requires that the safety and activation conditions applied to the other engine(s) are all met,
and if the activation logic encoded on the electronic chip of one of the engines switches to the deactivated state, the activation logic encoded on the electronic chip of the other engine(s) automatically does so as well; and
for each engine, switching the activation logic encoded on the electronic chip from the armed state to the first and then to the second intermediate state takes place automatically when a first portion and then a second portion, different from the first one, of at least one of the safety and activation conditions are met.

2. The method according to claim 1 , wherein switching the activation logic encoded on the electronic chip from the second intermediate state to the activated state takes places on one of the engines if the activation logic of the other engine(s) is(are) in said second intermediate state or in the activated state.

3. The method according to claim 1 , wherein after the electronic chip receives an order from the pilot, the activation logic encoded on the electronic chip switches from the second intermediate state to the deactivated state.

4. The method according to claim 1 , wherein if periodically checking, with the activation logic encoded on the electronic chip, at least one of the safety/activation conditions states that said second portion of the conditions is no longer met for at least one of the engines, or if the data relative to switching to the activated state of the activation logic encoded on the electronic chip of such motor sent to the other engine(s) through said exchange digital link states that the activation logic encoded on the electronic chip thereof is the first intermediate state, whereas the activation logic encoded on the electronic chip of the other engine(s) is the activated state, the latter switches to the first intermediate state.

5. The method according to claim 1 , wherein if the step of periodically checking states that said first portion of the conditions is no longer met for at least one of the engines, when the activation logic encoded on the electronic chip is in the first intermediate state, said activation logic encoded on the electronic chip switches to the armed state.

6. The method according to claim 1 , wherein switching the activation logic encoded on the electronic chip from any one of the first intermediate state and second intermediate state to the deactivated state takes place when the electronic chip receives the deactivation order issued by the pilot.

Assignees

• Safran Aircraft Engines
• Safan Aircraft Engines

Inventors

• Nobelen Florent

Classifications

• F02C9/16

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title

• F05D2270/304

  Spool rotational speed · CPC title

• B64D31/12 Primary

  for equalising or synchronising power plants · CPC title

• F02C9/42

  specially adapted for the control of two or more plants simultaneously · CPC title

• F05D2270/301

  Pressure · CPC title