Alternating starter use during multi-engine motoring
A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.
1. A system for alternating starter use during multi-engine motoring in an aircraft, the system comprising:
a first engine starting system of a first engine; and
a first controller in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine based on one or more adjustments to a baseline dry motoring profile to shift timing between the first engine and the second engine.
2. The system as in claim 1 , wherein control of the first engine starting system is based on one or more of: an ambient air temperature, an ambient pressure, an oil temperature, engine drag, and parasitic factors.
3. The system as in claim 1 , wherein a power source of the motoring includes a pneumatic or electric power source from at least one of: an auxiliary power unit of the aircraft, a ground cart, a cross engine supply, or a stored energy system.
4. The system as in claim 1 , wherein the first engine starting system is controlled based on the first controller commanding one or more adjustments to the baseline dry motoring profile to shift timing of use of compressed air to drive a first air turbine starter.
5. The system as in claim 1 , wherein the first controller is configured to coordinate with the second controller to control the first engine starting system and the second engine starting system of the second engine.
6. The system as in claim 5 , wherein the first controller is configured to alternate supplying power from a power source between the first engine starting system and the second engine starting system.
7. A system of an aircraft, the system comprising:
a compressed air source operable to supply compressed air;
a first engine system comprising a first gas turbine engine, a first air turbine starter, and a first controller configured to control delivery of the compressed air to the first air turbine starter during motoring of the first gas turbine engine;
a second engine system comprising a second gas turbine engine, a second air turbine starter, and a second controller configured to control delivery of the compressed air to the second air turbine starter during motoring of the second gas turbine engine; and
at least one engine control interface configured to cause supply of the compressed air to alternate between the first air turbine starter and the second air turbine starter to intermittently accelerate and decelerate the first gas turbine engine with respect to the second gas turbine engine, wherein the at least one engine control interface is configured to coordinate control, via the first controller and the second controller, alternating supply of the compressed air between the first air turbine starter and the second air turbine starter by commanding one or more adjustments to a baseline dry motoring profile to shift timing of use of the compressed air between the first engine system and the second engine system.
8. The system of claim 7 , wherein the system is configured to coordinate control, via the first controller and the second controller, the alternating supply of the compressed air between the first air turbine starter and the second air turbine starter based on one or more of: an ambient air temperature, an ambient pressure, an oil temperature, engine drag, and parasitic factors.
9. The system of claim 7 , wherein the system further comprises a first air starter valve and a second air starter valve, and the system is configured to coordinate control, via the first controller and the second controller, the alternating supply of the compressed air between the first air turbine starter and the second air turbine starter based on one or more of: an engine speed, a starter speed, a starter valve position, a starter air pressure, a rate of speed change, a rate of starter valve position change, and a rate of starter air pressure change.
10. The system of claim 7 , further comprising a first starter air valve configured to control the first air turbine starter and a second starter air valve configured to control the second air turbine starter.
11. The system of claim 10 , wherein the system is configured to coordinate control of the first starter air valve through the first controller and the second starter air valve through the second controller.
12. The system of claim 11 , wherein a first engine control interface is configured to buffer communication of the first engine system from an aircraft level communication, a second engine control interface is configured to buffer communication of the second engine system from the aircraft level communication, and the first engine control interface is configured to communicate with the second engine control interface.