Gas turbine engine system wear reduction
An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, where the sub-idle fuel burn schedule includes a reduction of an idle fuel burn schedule. The control system is configured to operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft.
1. An engine system for an aircraft, the engine system comprising:
a first gas turbine engine;
a second gas turbine engine;
a control system configured to:
operate the first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, the sub-idle fuel burn schedule comprising a reduction of an idle fuel burn schedule;
operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft;
track a sub-idle time of the first and second gas turbine engines; and
alternate the designation of the first gas turbine engine and the second gas turbine engine to substantially balance the sub-line time of the first and second gas turbine engines for the aircraft.
2. The engine system of claim 1 , wherein landing is detected based on detecting weight-on-wheels of the aircraft after transitioning from a descend phase of flight.
3. The engine system of claim 1 , wherein the control system is further configured to operate the first gas turbine engine with the sub-idle fuel burn schedule during a taxi-to-gate phase of the aircraft.
4. The engine system of claim 1 , wherein at least one engine bleed schedule is adjusted corresponding to the sub-idle fuel burn schedule to control a compressor work distribution during sub-idle operation.
5. The engine system of claim 4 , wherein adjustment to the at least one engine bleed schedule increases an engine bleed flow to at least one environment control system of the aircraft during sub-idle operation.
6. The engine system of claim 1 , wherein the control system comprises one or more of an engine controller and an aircraft controller.
7. A method of engine system control, the method comprising:
operating a first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of an aircraft, the sub-idle fuel burn schedule comprising a reduction of an idle fuel burn schedule;
operating a second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft;
tracking a sub-idle time of the first and second gas turbine engines; and
alternating the designation of the first gas turbine engine and the second gas turbine engine to substantially balance the sub-idle time of the first and second gas turbine engines for the aircraft.
8. The method of claim 7 , wherein landing is detected based on detecting weight-on-wheels of the aircraft after transitioning from a descend phase of flight.
9. The method of claim 7 , wherein the first gas turbine engine is operated with the sub-idle fuel burn schedule during a taxi-to-gate phase of the aircraft.
10. The method of claim 7 , further comprising:
adjusting at least one engine bleed schedule corresponding to the sub-idle fuel burn schedule to control a compressor work distribution during sub-idle operation.
11. The method of claim 10 , wherein adjusting the at least one engine bleed schedule increases an engine bleed flow to at least one environment control system of the aircraft during sub-idle operation.
12. An engine system for an aircraft, the engine system comprising:
a first gas turbine engine;
a second gas turbine engine;
a control system configured to:
operate the first gas turbine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, the sub-idle fuel burn schedule comprising a reduction of an idle fuel burn schedule; and
operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft, wherein at least one engine bleed schedule is adjusted corresponding to the sub-idle fuel burn schedule to control a compressor work distribution during sub-idle operation, and adjustment to the at least one engine bleed schedule increases an engine bleed flow to at least one environment control system of the aircraft during sub-idle operation.
13. The engine system of claim 12 , wherein landing is detected based on detecting weight-on-wheels of the aircraft after transitioning from a descend phase of flight.
14. The engine system of claim 12 , wherein the control system is further configured to operate the first gas turbine engine with the sub-idle fuel burn schedule during a taxi-to-gate phase of the aircraft.
15. The engine system of claim 12 , wherein the control system comprises one or more of an engine controller and an aircraft controller.