System and method for cooling the brakes of landing gear of an aircraft
A system for cooling the brakes of a brake system of a landing gear of an aircraft, including: a compressor configured to generate a pressurized airflow, the compressor including at least one air outlet, and an air jet pump including: a pump tube including a first end connected to the air outlet and a second end, the pump tube being designed to carry the pressurized airflow between the first and second ends, and a plurality of injectors connected to the second end of the pump tube, and configured to inject the pressurized airflow.
1. A cooling system for cooling brakes of a brake system of a landing gear of an aircraft, comprising:
a compressor configured to generate a pressurized air flow, said compressor comprising at least one air outlet, and
an air jet pump comprising:
a pump tube comprising a first end connected to said air outlet and a second end, said pump tube being designed to convey said pressurized air flow between the first and second ends, and
a plurality of injectors connected to said second end of the pump tube, and configured to inject said pressurized air flow,
wherein the plurality of injectors comprises a central injector arranged as an extension of the second end of the pump tube and a plurality of intermediate injectors arranged 360º around said central injector.
2. The cooling system according to claim 1 , wherein each injector has a cross-sectional restriction along a path of the pressurized air flow.
3. The cooling system according to claim 1 , wherein the plurality of injectors are arranged circumferentially and centred on the second end of the pump tube.
4. The cooling system according to claim 1 , wherein the plurality of injectors comprises a plurality of external injectors arranged 360° around said intermediate injectors.
5. The cooling system according to claim 4 , wherein the plurality of external injectors and the plurality of intermediate injectors are arranged in a staggered pattern around the second end of the pump tube.
6. The cooling system according to claim 1 , wherein at least one or each injector is elbow shaped.
7. The cooling system according to claim 1 , wherein the compressor is an electric compressor.
8. A landing gear of an aircraft comprising:
at least one wheel;
a brake system comprising brakes adapted to slow or stop the rotation of said at least one wheel; and
a cooling system according to claim 1 .
9. The landing gear according to claim 8 , wherein the compressor of the cooling system is arranged remotely from an area near the brakes.
10. The landing gear according to claim 8 , wherein each injector is arranged outside a rim of the wheel.
11. The landing gear according to claim 8 , wherein each injector is arranged inside a rim of the wheel.
12. A method for cooling the brakes of a brake system of a landing gear of an aircraft, the landing gear including at least one wheel, a brake system comprising brakes adapted to slow or stop the rotation of said at least one wheel, and a cooling system according to claim 1 , the method comprising:
compressing, by the compressor, an air flow so as to generate a pressurized air flow;
conveying the pressurized air flow, by the pump tube, to an area near the brakes;
injecting, by each injector, the pressurized air flow into said area near the brakes; and
sucking an air flow from said area near the brakes.