Failsafe multimode clutch assemblies for rotorcraft
A failsafe multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having input and output races. The freewheeling unit has a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly must be energized to shift the bypass assembly from the engaged position to a disengaged position. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.
1. A powertrain for a rotorcraft, the powertrain comprising:
a main drive system including a main engine;
a secondary engine; and
a failsafe multimode clutch assembly positioned between the main drive system and the secondary engine, the clutch assembly including:
a freewheeling unit having an input race coupled to the main drive system and an output race coupled to the secondary engine, the freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race;
a bypass assembly having an engaged position in which the bypass assembly couples the input and output races of the freewheeling unit and a disengaged position in which the bypass assembly does not couple the input and output races of the freewheeling unit; and
an actuator assembly having a default configuration in which a mechanical biasing element provides an engagement force that maintains the bypass assembly in the engaged position and an energized configuration in which a disengagement element provides a disengagement force that overcomes the engagement force and shifts the bypass assembly from the engaged position to the disengaged position;
wherein, in the disengaged position of the bypass assembly, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer from the input race to the output race; and
wherein, in the engaged position of the bypass assembly, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer between the input and output races.
2. The powertrain as recited in claim 1 wherein the main engine further comprises a first gas turbine engine and wherein the secondary engine further comprises a second gas turbine engine.
3. The powertrain as recited in claim 1 wherein the main engine further comprises a gas turbine engine and wherein the secondary engine further comprises an electric motor.
4. The powertrain as recited in claim 1 wherein the secondary engine is configured to generate between about 5 percent and about 20 percent of the power of the main engine.
5. The powertrain as recited in claim 1 wherein the secondary engine is configured to generate between about 10 percent and about 15 percent of the power of the main engine.
6. The powertrain as recited in claim 1 wherein the default configuration of the actuator assembly further comprises an unenergized state of the actuator assembly.
7. The powertrain as recited in claim 1 wherein the engagement force of the mechanical biasing element is configured to shift the bypass assembly from the disengaged position to the engaged position when the disengagement force of the disengagement element is not provided.
8. The powertrain as recited in claim 1 wherein the actuator assembly further comprises a liner and a piston, the piston slidably disposed relative to the liner and coupled to the bypass assembly; and
wherein, the mechanical biasing element is positioned between the liner and the piston to bias the bypass assembly toward the engaged position.
9. The powertrain as recited in claim 1 wherein the mechanical biasing element further comprises a wave spring.
10. The powertrain as recited in claim 1 wherein the disengagement element further comprises a pressure switch.
11. The powertrain as recited in claim 10 wherein the pressure switch further comprises a hydraulic switch.
12. The powertrain as recited in claim 10 wherein the pressure switch further comprises a compressed air switch.
13. The powertrain as recited in claim 1 wherein the disengagement element further comprises an electric switch.
14. The powertrain as recited in claim 1 wherein the default configuration of the actuator assembly further comprises an unenergized state of the disengagement element.
15. A rotorcraft comprising:
a main rotor coupled to a main drive system including a main engine;
a secondary engine; and
a failsafe multimode clutch assembly positioned between the main drive system and the secondary engine, the clutch assembly including:
a freewheeling unit having an input race coupled to the main drive system and an output race coupled to the secondary engine, the freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race;
a bypass assembly having an engaged position in which the bypass assembly couples the input and output races of the freewheeling unit and a disengaged position in which the bypass assembly does not couple the input and output races of the freewheeling unit; and
an actuator assembly having a default configuration in which a mechanical biasing element provides an engagement force that maintains the bypass assembly in the engaged position and an energized configuration in which a disengagement element provides a disengagement force that overcomes the engagement force and shifts the bypass assembly from the engaged position to the disengaged position;
wherein, in the disengaged position of the bypass assembly, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer from the input race to the output race; and
wherein, in the engaged position of the bypass assembly, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer between the input and output races.
16. The rotorcraft as recited in claim 15 wherein, in a preflight configuration, the bypass assembly is in the disengaged position, the main engine is not operating and the secondary engine provides power to at least one rotorcraft accessory.
17. The rotorcraft as recited in claim 15 wherein, in an enhanced power configuration, the bypass assembly is in the engaged position, the main engine provides power to the main drive system and the secondary engine provides power to at least one rotorcraft accessory and to the main drive system through the clutch assembly.
18. The rotorcraft as recited in claim 15 wherein, in a high efficiency configuration, the bypass assembly is in the engaged position, the secondary engine is in standby mode and the main engine provides power to the main drive system and to at least one rotorcraft accessory through the clutch assembly.
19. The rotorcraft as recited in claim 15 wherein, in an enhanced autorotation configuration, the bypass assembly is in the engaged position, the main engine is not operating and the secondary engine provides power to the main drive system through the clutch assembly.