Systems and methods for reducing oxidation of friction disks
A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a coolant loop coupled to the braking assembly, with the coolant loop being configured to circulate liquid coolant from the braking assembly. That is, the coolant loop may be configured to reduce the temperature of the braking assembly, thus reducing the rate/extent of oxidation of the friction disks and potentially enabling the concentration of oxygen around the braking assembly to be reduced.
1. A system for reducing oxidation of a friction disk, the system comprising:
a braking assembly of a wheel assembly, the braking assembly comprising a torque tube and the friction disk; and
a coolant loop coupled in heat exchange communication with the braking assembly, wherein the coolant loop is configured to circulate liquid coolant such that heat is transferred from the friction disk to the liquid coolant, wherein the coolant loop comprises:
a supply line configured to deliver the liquid coolant to a coolant channel defined by the braking assembly, wherein the torque tube defines at least a portion of the coolant channel; and
an outlet line configured to deliver the liquid coolant away from the coolant channel of the braking assembly.
2. The system of claim 1 , wherein the system further comprises a conduit coupled in selectable fluid providing communication with the braking assembly, wherein the conduit is configured to deliver inert fluid to the braking assembly.
3. The system of claim 2 , wherein the wheel assembly is configured to limit convective ambient airflow around the friction disk of the braking assembly.
4. The system of claim 3 , wherein an outboard wheel portion of a wheel of the wheel assembly is continuous to limit convective ambient airflow around the friction disk of the braking assembly.
5. The system of claim 3 , wherein the wheel assembly further comprises a heat shield, wherein the heat shield is configured to limit ambient airflow around the friction disk of the braking assembly.
6. The system of claim 2 , wherein the inert fluid comprises a nitrogen-enriched air stream and an inert fluid source comprises a membrane configured to separate the nitrogen-enriched air stream from air.
7. The system of claim 6 , wherein delivery of the nitrogen-enriched air stream to the braking assembly via the conduit is actuated in response to determining a status of the braking assembly, wherein the status pertains to a likelihood of oxidation of the friction disk.
8. An aircraft comprising:
a landing gear comprising a wheel assembly;
a braking assembly operatively coupled to the wheel assembly of the landing gear, the braking assembly comprising a friction disk;
a heat exchanger coupled to the landing gear; and
a coolant loop extending between the braking assembly and the heat exchanger, wherein the coolant loop is configured to circulate liquid coolant between the braking assembly and the heat exchanger such that heat is transferred from the friction disk to the liquid coolant, wherein the coolant loop comprises a liquid coolant pump configured to drive circulation of the liquid coolant.
9. The aircraft of claim 8 , wherein the braking assembly comprises a torque tube, wherein the torque tube defines at least a portion of the coolant loop.
10. The aircraft of claim 9 , wherein the heat exchanger is mounted to a strut of the landing gear.
11. The aircraft of claim 8 , wherein the aircraft further comprises a conduit coupled in selectable fluid providing communication with the braking assembly, wherein the conduit is configured to deliver inert fluid to the braking assembly.
12. The aircraft of claim 11 , wherein the wheel assembly is configured to limit convective ambient airflow around the friction disk of the braking assembly.
13. The aircraft of claim 12 , wherein an outboard wheel portion of a wheel of the wheel assembly is continuous to limit convective ambient airflow around the friction disk of the braking assembly.
14. The aircraft of claim 12 , wherein the wheel assembly further comprises a heat shield, wherein the heat shield is configured to limit ambient airflow around the friction disk of the braking assembly.
15. The aircraft of claim 11 , wherein the inert fluid comprises a nitrogen-enriched air stream and an inert fluid source comprises a membrane configured to separate the nitrogen-enriched air stream from air.
16. The aircraft of claim 15 , further comprising an on-board fuel tank inerting system, wherein the inert fluid source is the on-board fuel tank inerting system.
17. The aircraft of claim 16 , wherein delivery of the nitrogen-enriched air stream to the braking assembly via the conduit is actuated in response to determining a status of the braking assembly, wherein the status pertains to a likelihood of oxidation of the friction disk.