Aircraft propulsion system with inlet air monitoring system and method
A method of producing an operational data for an aircraft turbine engine is provided that including: sensing an inlet airflow to an aircraft turbine engine for CMAS particulate matter, the sensing performed during one or more ground portions of a flight operational cycle of the turbine engine, the sensing producing sensor signals indicative of the presence or absence of the CMAS particulate matter; determining a presence or absence of an exposure by the turbine engine to a CMAS environment based on the sensor signals; and producing an operational data indicative of the presence or absence of said exposure by the turbine engine to said CMAS environment.
1. A method of producing cumulative operational data for an aircraft turbine engine, comprising:
(a) sensing an inlet airflow to an aircraft turbine engine for calcium-magnesium-alumino-silicate (CMAS) particulate matter, the sensing performed during one or more ground portions of a flight operational cycle of the turbine engine, the sensing producing sensor signals indicative of the presence or absence of the CMAS particulate matter;
(b) determining a presence or absence of an exposure by the turbine engine to a CMAS environment based on the sensor signals; and
(c) repeating steps (a)-(b) over a predetermined amount of time and producing cumulative operational data indicative of the presence or absence of said exposure by the turbine engine to said CMAS environment over said predetermined amount of time.
2. The method of claim 1 , wherein the sensing is performed using an inlet debris monitoring system (IDMS) that uses a pair of rings to sense changes in electrostatic charge.
3. The method of claim 2 , wherein the determining includes evaluating the sensor signals relative to a baseline.
4. The method of claim 3 , wherein the baseline is a fixed value based on sensing data.
5. The method of claim 4 , wherein the operational data is collected over a plurality of flights of the turbine engine.
6. The method of claim 3 , wherein the baseline is indicative of a density of said CMAS particulate matter within the inlet airflow that is not associated with deleterious effect to the turbine engine.
7. The method of claim 1 , wherein the step of producing said cumulative operational data includes producing flags indicative of the presence or absence of a CMAS environment.
8. The method of claim 1 , wherein the step of producing said cumulative operational data includes producing cumulative data relating to a magnitude of a CMAS environment to which the turbine engine is exposed.
9. The method of claim 1 , wherein the step of producing said cumulative operational data includes producing data relating to a cumulative exposure of the turbine engine to one or more said CMAS environments.
10. The method of claim 9 , wherein the cumulative exposure is determined based on said sensor signals collected over a plurality of said flight operational cycles of the turbine engine.
11. The method of claim 9 , wherein the cumulative exposure is determined based on said sensor signals collected over said predetermined amount of time, elapsed during a plurality of said flight operational cycles of the turbine engine.
12. The method of claim 1 , wherein the one or more ground portions of a flight operational cycle of the turbine engine includes a ground idle portion and a takeoff portion, and the sensing is performed only during the ground idle portion and the takeoff portion.
13. The method of claim 1 , wherein the one or more ground portions of a flight operational cycle of the turbine engine includes a takeoff portion and a landing portion, and the sensing is performed only during the takeoff portion and the landing portion.
14. The method of claim 1 , wherein the one or more ground portions of a flight operational cycle of the turbine engine includes a takeoff portion, and the sensing is performed only during the takeoff portion.
15. A system for producing cumulative operational data for an aircraft turbine engine having an airflow inlet, comprising:
an inlet debris monitoring system (IDMS) configured to sense an inlet air flow to the turbine engine for calcium-magnesium-alumino-silicate (CMAS) particulate matter, the IDMS configured to produce sensor signals indicative of the presence or absence of the CMAS particulate matter;
a controller in communication with the IDMS and a non-transitory memory storing instructions, which instructions when executed cause the controller to:
control the IDMS to sense the inlet air flow for CMAS particulate matter during one or more ground portions of a flight operational cycle of the turbine engine, and produce the sensor signals indicative of the presence or absence of the CMAS particulate matter;
determine a presence or absence of an exposure by the turbine engine to a CMAS environment based on the sensor signals; and
produce an operational data indicative of the presence or absence of said exposure by the turbine engine to said CMAS environment,
wherein in the production of said operational data indicative of the presence or absence of said exposure to said CMAS environment, the instructions cause the controller to produce data relating to a cumulative exposure of the turbine engine to one or more CMAS environments.
16. The system of claim 15 , wherein in the determination of the presence or absence of said exposure by the turbine engine to said CMAS environment based on the sensor signals, the instructions cause the controller to evaluate the sensor signals relative to a baseline value.
17. The system of claim 15 , wherein in the production of said operational data indicative of the presence or absence of said exposure to said CMAS environment, the instructions cause the controller to produce a flag indicative of the presence or absence of a CMAS environment.
18. The system of claim 15 , wherein in the production of said operational data indicative of the presence or absence of said exposure to said CMAS environment, the instructions cause the controller to produce data relating to a magnitude of a said CMAS environment to which the turbine engine is exposed.
19. The system of claim 15 , wherein the one or more ground portions of a flight operational cycle of the turbine engine includes a ground idle portion and a takeoff portion, and the controller controls the IDMS to sense the inlet air flow for CMAS particulate matter only during the ground idle portion.