Braking control assembly for an aircraft gas turbine engine and method of using same
An assembly for a gas turbine engine of an aircraft includes a rotational assembly, a starter generator, and a control relay. The starter generator is coupled with the rotational assembly. The starter generator is configured to selectively drive rotation of the rotational assembly. The starter generator includes a motor winding including a first electrical terminal and a second electrical terminal. The control relay includes a switch electrically connected to the first electrical terminal. The switch is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal is electrically isolated from the second electrical terminal through the switch. In the second contact position, the first electrical terminal is electrically connected to the second electrical terminal through the switch such that a closed electrical circuit is formed through the motor winding, the first electrical terminal, the second electrical terminal, and the switch.
1 . An assembly for a gas turbine engine of an aircraft, the assembly comprising:
a rotational assembly;
a starter generator coupled with the rotational assembly, the starter generator is configured to selectively drive rotation of the rotational assembly, and the starter generator includes a motor winding including a first electrical terminal and a second electrical terminal;
a control relay including a variable resistor and a switch, the switch electrically connected to the first electrical terminal, the switch is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal is electrically isolated from the second electrical terminal through the switch, and in the second contact position, the first electrical terminal is electrically connected to the second electrical terminal through the switch such that a closed electrical circuit is formed through the motor winding, the first electrical terminal, the switch, and the second electrical terminal, and in the second contact position, the variable resistor is configured to selectively vary an electrical resistance between the first electrical terminal and the second electrical terminal;
the starter generator further configured to resist rotation of the rotational assembly with the switch in the second contact position; and
a controller connected in communication with the control relay, the controller includes a processor in communication with a non-transitory memory storing instructions, the storing instructions, when executed by the processor, cause the processor to:
control the control relay to position the switch in the first contact position or the second contact position; and
control the variable resistor to control the electrical resistance between the first electrical terminal and the second electrical terminal.
2 . The assembly of claim 1 , further comprising a battery electrically connected to the starter generator and the switch such that, in the first contact position, the battery is configured to supply electrical power to the starter generator.
3 . The assembly of claim 1 , wherein the starter generator is configured to drive rotation of the rotational assembly with the switch in the first contact position.
4 . The assembly of claim 1 , wherein the starter generator is coupled with the rotational assembly by a gearbox.
5 . The assembly of claim 1 , wherein the rotational assembly includes a shaft, a bladed compressor rotor, and a bladed turbine rotor, and the shaft interconnects the bladed compressor rotor and the bladed turbine rotor.
6 . The assembly of claim 5 , further comprising a main generator coupled with the rotational assembly, the rotational assembly configured to drive rotation of the main generator.
7 . The assembly of claim 1 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during a shutdown process for the gas turbine engine.
8 . The assembly of claim 7 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during the shutdown process for the gas turbine engine when a rotation speed of the rotational assembly decreases to or below a rotation speed threshold value.
9 . The assembly of claim 1 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during a flight condition of the aircraft.
10 . The assembly of claim 1 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during an overspeed condition of the rotational assembly.
11 . An assembly for a gas turbine engine of an aircraft, the assembly comprising:
a rotational assembly;
a starter generator coupled with the rotational assembly, the starter generator is configured to selectively drive rotation of the rotational assembly, and the starter generator includes a motor winding including a first electrical terminal and a second electrical terminal;
a control relay including a switch electrically connected to the first electrical terminal, the switch is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal is electrically isolated from the second electrical terminal through the switch, and in the second contact position, the first electrical terminal is electrically connected to the second electrical terminal through the switch such that a closed electrical circuit is formed through the motor winding, the first electrical terminal, the switch, and the second electrical terminal; and
a controller connected in communication with the control relay, the controller includes a processor in communication with a non-transitory memory storing instructions, the storing instructions, when executed by the processor, cause the processor to control the control relay to position the switch in the first contact position or the second contact position;
wherein the starter generator is configured to drive rotation of the rotational assembly with the switch in the first contact position; and
wherein the control relay includes a variable resistor, and with the switch in the second contact position, the variable resistor is configured to selectively vary an electrical resistance between the first electrical terminal and the second electrical terminal.
12 . The assembly of claim 11 , further comprising a battery electrically connected to the starter generator and the switch such that, in the first contact position, the battery is configured to supply electrical power to the starter generator.
13 . The assembly of claim 11 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during a shutdown process for the gas turbine engine.
14 . The assembly of claim 11 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during a flight condition of the aircraft.
15 . The assembly of claim 11 , wherein the instructions, when executed by the processor, further cause the processor to control the control relay to position the switch in the second contact position during an overspeed condition of the rotational assembly.