Method of synchronizing the engines of an aircraft

Patent metadata

Field	Value
Publication number	US-9415877-B2
Application number	US-201414200130-A
Country	US
Kind code	B2
Filing date	Mar 7, 2014
Priority date	Sep 9, 2011
Publication date	Aug 16, 2016
Grant date	Aug 16, 2016

Abstract

A method of synchronizing engines of an airplane in accordance with at least one activation logic ( 10, 10 ′) defining a deactivated state ( 20 ), a primed state ( 22 ), and at least one activated state ( 16, 18 ), and comprising:
passing ( 32 ) synchronization from the deactivated state to the primed state when a pilot of the airplane issues an activation order; passing ( 36 ) synchronization from the primed state to the activated state when at least certain safety and/or activation conditions are satisfied; and passing ( 24, 34 ) synchronization from the activated or primed state to the deactivated state when the pilot issues a deactivation order or whenever at least some of the safety conditions are not satisfied.

First claim

The invention claimed is:

1. A method of synchronizing engines of an airplane by an electronic chip encoding at least one activation logic for verifying safety and/or activation conditions in order to apply synchronization to the engines, wherein the activation logic defines synchronization states of the engines including at least a deactivated state, a primed state, and an activated state, the method comprising:
receiving, with the electronic chip, an activation order issued by a pilot of the airplane;
outputting, with the activation logic encoded on the electronic chip, a command to pass a synchronization state of the engines from the deactivated state to the primed state when the activation order issued by the pilot is received;
determining, with the activation logic encoded on the electronic chip, whether the safety and/or activation conditions are satisfied or not satisfied, by periodically verifying whether the safety and/or activation conditions meet predetermined thresholds or predetermined operation states of the engines or of the airplane;
outputting, with the activation logic encoded on the electronic chip, a command to pass the synchronization state of the engines from the primed state to the activated state when certain of the safety and/or activation conditions are satisfied;
receiving, with the electronic chip, a deactivation order issued by the pilot, or determining that certain of the safety conditions are not satisfied; and
outputting, with the activation logic encoded on the electronic chip, a command to pass the synchronization state of the engines from the activated state or the primed state to the deactivated state when the deactivation order issued by the pilot is received or whenever it is determined that the certain of said safety conditions are not satisfied.

2. A method according to claim 1 , wherein:
the safety and/or activation conditions for application to synchronization comprise safety conditions for activating synchronization and synchronization activation conditions that are different from safety conditions; and
the activation logic includes passing synchronization from the activated state to the primed state whenever certain activation conditions are not satisfied.

3. A method according to claim 1 , wherein the conditions for activating synchronization to the activated state differ as a function of the initially deactivated or primed state of the synchronization.

4. A method according to claim 1 , wherein the activation logic defines two distinct activated states, comprising a guaranteed activated state in which all of the activation conditions are satisfied and a non-guaranteed activated state in which only some of said activation conditions are satisfied.

5. A method according to claim 1 , wherein:
the activation logic defines two distinct activated states, comprising a guaranteed activated state in which all of the activation conditions are satisfied and a non-guaranteed activated state in which only some of said activation conditions are satisfied, and
the activation logic includes passing synchronization from the primed state to the non-guaranteed activated state when only a predefined portion of the activation conditions are satisfied, and to the guaranteed activated state when all of the activation conditions are satisfied.

6. A method according to claim 1 , wherein:
the activation logic defines two distinct activated states, comprising a guaranteed activated state in which all of the activation conditions are satisfied and a non-guaranteed activated state in which only some of said activation conditions are satisfied, and
synchronization passes from the non-guaranteed activated state to the guaranteed activated state, and/or vice versa, as a function of changes occurring in the results of said periodic verifying of activation conditions.

7. A method according to claim 1 , wherein:
for each engine:
the passing of synchronization from the primed state to the activated state is performed by means of a transient ready-to-activate state;
synchronization is passed from the activated state to the ready-to-activate state when certain safety and/or activation conditions are satisfied;
before any passing of synchronization from the ready-to-activate state to the activated state, account is taken for each engine of the activated or ready-to-activate state and this data is exchanged between the engines; and
synchronization is passed from the ready-to-activate state to the activated state on one of the engines, when the other engine or engines is, or are, in the ready-to-activate state or in the activated state.

8. A method according to claim 4 , wherein the activation logic defines an additional state which is a ready-to-activate state that is transient, and distinct from said deactivated, primed, non-guaranteed activated, and guaranteed activated states respectively, said ready-to-activate state taking account of the state of one of the engines relative to the other(s) depending on whether or it is in the guaranteed activated state, such that:
when one of the engines passes to the activated state, the other engine(s) also pass(es) to the activated state automatically; and
passing the synchronization of one of the engines to the guaranteed activated state requires all of the safety and activation conditions of the other engine(s) to be satisfied.

9. A method according to claim 1 , wherein the engines are two-spool engines, each having a LP, low pressure, spool and a HP, high pressure, spool, and synchronization of the LP spools of the engines is activated in accordance with a first activation logic and synchronization of the HP spools of the engines is activated in accordance with a second activation logic, in such a manner that the conditions for synchronizing the LP spools are different from the conditions for synchronizing the HP spools.

10. A method according to claim 9 , wherein the conditions for synchronizing the LP spools comprise, at least: a safety condition for activating synchronization and a synchronization activation condition and the synchronization conditions for the HP spools comprise, at least: a safety condition for activating synchronization and a plurality of cumulative synchronization activation conditions .

11. A method according to claim 9 , wherein the conditions for synchronizing the LP spools are different from the conditions for synchronizing the HP spools.

12. A method according to claim 9 , wherein the conditions for synchronizing the LP and/or HP spools comprise one or more of the following conditions:
the difference between the setpoints for the speeds of the LP or HP rotors of the engines is less than 5%;
no fault has been detected that might affect the health of the engines or that might generate risks for the airplane;
the difference between the measured speeds of the LP or HP rotors of the engines is less than 5%;
the difference between the speed setpoint and the measured speed for each LP or HP rotor is less than 5%;
at least one of the engines is idling; and
the airplane is in flight and is neither in a takeoff stage nor in a climbing stage.

13. A method according to claim 12 , wherein the synchronization passes from the activated state to the deactivated state when at least one of the conditions:
the difference between the setpoints for the speeds of the LP or HP rotors of the engines is less than 5%,
no fault has been detected that might affect the health of the engines or that might generate risks for the airplane, and
the difference between the measured speeds of the LP or HP rotors of the engines is less than 5%, is not satisfied.

1

Assignees

• Snecma

Inventors

• Nobelen Florent
• Djelassi Cedrik

Classifications

• 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