Monitoring of a filter of the fuel-supply system of an aircraft engine
View Patent ↗A monitoring method for monitoring a filter of a feed circuit for feeding an aircraft engine with fuel, the method including: detecting clogging of the filter; issuing an indication message; determining a current stage from among a plurality of successive stages of a mission of the aircraft, including at least a stage during which clogging of the filter is not capable of being caused by ice, and a stage during which clogging of the filter might be caused by ice; and in response to detecting clogging, determining the type of clogging as a function of the current stage; wherein during the issuing an indication message, the message that is issued depends on the type of clogging.
1. A monitoring method for monitoring a filter of a feed circuit for feeding an aircraft engine with fuel, the method comprising:
detecting clogging of the filter;
issuing an indication message;
defining a plurality of successive stages of a mission of the aircraft, comprising at least a stage during which clogging of the filter is not capable of being caused by ice, and a stage during which clogging of the filter might be caused by ice;
determining a current stage from among said plurality of successive stages; and
in response to detecting clogging, determining a type of clogging as a function of the current stage from a normal clogging, an extreme clogging, and an ice clogging;
wherein during the issuing an indication message, the message that is issued depends on the type of clogging.
2. A monitoring method according to claim 1 , wherein, when the current stage is a stage during which clogging of the filter might be caused by ice, the determining a type of clogging includes testing for icing conditions.
3. A monitoring method according to claim 2 , further comprising after the testing for icing conditions, and if the icing conditions are found to exist, measuring a detection duration during which clogging has been detected, wherein:
if the detection duration is longer than a predetermined time-out duration, the type of clogging is determined to be extreme clogging and the indication message that is issued indicates that maintenance is necessary; and
if the detection duration is shorter than the time-out duration, the type of clogging is determined as being ice clogging and no indication message indicating a need for maintenance is issued.
4. A monitoring method according to claim 2 , wherein, after the testing for icing conditions, if the icing conditions are found not to exist, the type of clogging is determined as being extreme clogging and the indication message issued indicates a need for maintenance.
5. A monitoring method according to claim 2 , wherein the stage during which clogging of the filter might be caused by ice is a stage during which the aircraft is taking off.
6. A monitoring method according to claim 1 , wherein, when the current stage is a stage during which clogging of the filter cannot be caused by ice, the type of the clogging is determined to be normal clogging or extreme clogging and the indication message that is issued indicates a need for maintenance.
7. A monitoring method according to claim 1 , wherein the determining a current stage includes at least one testing a condition for passing on to a following stage.
8. A monitoring method according to claim 1 , wherein the successive stages comprise a first stage during which the aircraft is on the ground prior to takeoff, a second stage during which the aircraft is taking off, a third stage during which the aircraft is in flight, and a fourth stage during which the aircraft is on the ground after landing.
9. A non-transitory computer readable medium including computer executable instructions configured to execute a monitoring method for monitoring a filter of a feed circuit for feeding an aircraft engine with fuel when executed by a computer, the monitoring method comprising:
detecting clogging of the filter;
issuing an indication message;
defining a plurality of successive stages of a mission of the aircraft, comprising at least a stage during which clogging of the filter is not capable of being caused by ice, and a stage during which clogging of the filter might be caused by ice;
determining a current stage from among said plurality of successive stages; and
in response to detecting clogging, determining a type of clogging as a function of the current stage from a normal clogging, an extreme clogging, and an ice clogging;
wherein during the issuing an indication message, the message that is issued depends on the type of clogging.
10. An electronic unit for controlling a turbine engine, the electronic unit comprising the non-transitory computer readable medium according to claim 9 .
11. An aircraft engine comprising a gas turbine and an electronic unit according to claim 10 .