Systems and methods for engine wear reduction
An engine may include a processor communicatively coupled to a pitch actuator configured to affect a pitch of a plurality of variable pitch blades and a secondary thrust effector device. The processor is configured to change the pitch of the plurality of variable pitch blades via the pitch actuator in response to changes in a target engine parameter a normal operating mode, detect a trigger condition for a wear reduction mode, and switch from the normal operating mode to the wear reduction mode, wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at a first angle, and the secondary thrust effector device is controlled in response to the changes in the target engine parameter.
1 . An engine system comprising:
a pitch actuator configured to affect a pitch of a plurality of variable pitch blades of an engine;
a secondary thrust effector device; and
a processor communicatively coupled to the pitch actuator and the secondary thrust effector device, the processor being configured to:
change the pitch of the plurality of variable pitch blades via the pitch actuator in response to changes in a target engine parameter in a normal operating mode;
detect a trigger condition for a wear reduction mode; and
in response to the trigger condition being detected, switch from the normal operating mode to the wear reduction mode, wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at a first angle, and the secondary thrust effector device is controlled in response to the changes in the target engine parameter to compensate for an effect of the pitch actuator on the target engine parameter, wherein, the trigger condition comprises the target engine parameter being within a predetermined range during a period of time.
2 . The system of claim 1 , wherein the trigger condition comprises a threshold altitude, a threshold Mach number, and/or a throttle position.
3 . The system of claim 1 , wherein the engine system further comprises a mechanical pitch-locking mechanism; and wherein in the wear reduction mode, the mechanical pitch-locking mechanism is engaged to limit pitching of the plurality of variable pitch blades.
4 . The system of claim 1 , wherein the pitch of the plurality of variable pitch blades is maintained at a first angle based on control signals sent from the processor to the pitch actuator.
5 . The system of claim 1 , wherein the plurality of variable pitch blades comprises fan blades of an open rotor engine.
6 . The system of claim 1 , wherein the secondary thrust effector device comprises a fuel injection controller, an electric motor generator, inlet guide vanes, outlet guide vanes, and/or bleed valves.
7 . The system of claim 1 , wherein the processor is further configured to:
detect an exit condition for the wear reduction mode, wherein the exit condition comprises a change of the target engine parameter exceeding an exit threshold; and
in response to detecting the exit condition, switch from the wear reduction mode to the normal operating mode.
8 . The system of claim 7 , wherein the processor is further configured to determine an engine parameter baseline based on values of the target engine parameter over a period of time, wherein the exit condition is detected based on the change from the engine parameter baseline.
9 . The system of claim 1 , wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at the first angle with changes of the target engine parameter of up to 5%.
10 . The system of claim 1 , wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at the first angle for at least five minutes, at least ten minutes, or at least twenty minutes.
11 . The system of claim 1 , wherein the target engine parameter is received from an auto-throttle system and/or determined based on a pilot throttle control.
12 . The system of claim 1 , wherein the target engine parameter is determined based on flight conditions measured by a sensor system and a target speed.
13 . The system of claim 1 , wherein the trigger condition of the wear reduction mode corresponds to a cruising condition of an aircraft of the engine system.
14 . The system of claim 1 , wherein the target engine parameter comprises at least one of thrust, speed, torque, power, pressure, or pressure ratio parameters.
15 . An engine system comprising:
a pitch actuator configured to affect a pitch of a plurality of variable pitch blades of an engine;
a secondary thrust effector device; and
a processor communicatively coupled to the pitch actuator and the secondary thrust effector device, the processor being configured to:
change the pitch of the plurality of variable pitch blades via the pitch actuator in response to changes in a target engine parameter in a normal operating mode;
detect a trigger condition for a wear reduction mode; and
in response to the trigger condition being detected, switch from the normal operating mode to the wear reduction mode, wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at a first angle, and the secondary thrust effector device is controlled in response to the changes in the target engine parameter to compensate for an effect of the pitch actuator on the target engine parameter, wherein in response to the same amount of change in the target engine parameter, the secondary thrust effector device is controlled to cause a greater effect on an output parameter of the engine in the wear reduction mode as compared to the normal operating mode.
16 . An engine system comprising:
a pitch actuator configured to affect a pitch of a plurality of variable pitch blades of an engine;
a secondary thrust effector device; and
a processor communicatively coupled to the pitch actuator and the secondary thrust effector device, the processor being configured to:
change the pitch of the plurality of variable pitch blades via the pitch actuator in response to changes in a target engine parameter in a normal operating mode;
detect a trigger condition for a wear reduction mode; and
in response to the trigger condition being detected, switch from the normal operating mode to the wear reduction mode, wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at a first angle, and the secondary thrust effector device is controlled in response to the changes in the target engine parameter to compensate for an effect of the pitch actuator on the target engine parameter,
wherein the processor is further configured to:
determine, while in the wear reduction mode, target pitch angles for the plurality of variable pitch blades based on flight conditions and the target engine parameter;
switch from the wear reduction mode to an adjustment mode when an average target pitch angle in a time window deviates from the first angle for more than a threshold amount; and
change, in the adjustment mode, the angles of the plurality of variable pitch blades from the first angle to the average target pitch angle; and
in response to the plurality of variable pitch blades being pitched to the average target pitch angle, switch to the wear reduction mode.
17 . An engine system comprising:
a pitch actuator configured to affect a pitch of a plurality of variable pitch blades of an engine;
a secondary thrust effector device; and
a processor communicatively coupled to the pitch actuator and the secondary thrust effector device, the processor being configured to:
change the pitch of the plurality of variable pitch blades via the pitch actuator in response to changes in a target engine parameter in a normal operating mode;
detect a trigger condition for a wear reduction mode; and
in response to the trigger condition being detected, switch from the normal operating mode to the wear reduction mode, wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at a first angle, and the secondary thrust effector device is controlled in response to the changes in the target engine parameter to compensate for an effect of the pitch actuator on the target engine parameter, wherein in the normal operating mode, the pitch actuator is in a closed command loop with the target engine parameter and the secondary thrust effector device is in an open command loop.
18 . An engine system comprising:
a pitch actuator configured to affect a pitch of a plurality of variable pitch blades of an engine;
a secondary thrust effector device; and
a processor communicatively coupled to the pitch actuator and the secondary thrust effector device, the processor being configured to:
change the pitch of the plurality of variable pitch blades via the pitch actuator in response to changes in a target engine parameter in a normal operating mode;
detect a trigger condition for a wear reduction mode; and
in response to the trigger condition being detected, switch from the normal operating mode to the wear reduction mode, wherein in the wear reduction mode, the pitch of the plurality of variable pitch blades is maintained at a first angle, and the secondary thrust effector device is controlled in response to the changes in the target engine parameter to compensate for an effect of the pitch actuator on the target engine parameter, wherein in the wear reduction mode, the secondary thrust effector device is in a closed command loop with the target engine parameter and the pitch actuator is in an open command loop.