Method for monitoring the engines of an aircraft
AssigneeAurbus Operations (S.A.S)
InventorAntoine PILON
Life of this patent
Estimating the term…
Abstract
A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.
Claims2
A method for monitoring the engines of an aircraft comprising at least two engines, a central processing unit associated with each engine and configured to measure the temperature of the exhaust gasses of the engine and an amplitude of vibrations of at least one rotor of the engine and the power of the engine, a plurality of onboard systems, a diagnostic device for the onboard systems of the aircraft configured to measure a value of at least one parameter of at least one onboard system of the aircraft, a display screen and a monitoring device connected to each of the central processing units and to the diagnostic device and to the screen,
- the method being implemented by the monitoring device, and comprising, for each engine, the steps:
- generating, by the monitoring device, if a loss of power of the engine is detected and if one of two conditions A or B is met, a signal indicative of severe damage of the engine, a message according to which an engine has suffered severe damage being displayed on a display screen on transmission, by the monitoring device, of the signal indicative of severe damage of the engine, where:
- condition A is met if at least:
- the value of at least one parameter of at least one onboard system of the aircraft is outside of an acceptable range of values;
- and
- condition B is met if at least:
- the temperature of the exhaust gasses of the engine is in excess of a predetermined value AND an amplitude of vibrations of at least one rotor of the engine is in excess of a predetermined value.
Dependencies are inferred from the claim text.