Anti-ice/de-ice system
An anti-ice/de-ice system includes a component having at least one flow channel extending therethrough, a pressurized air source, and an aerodynamic resonator. The pressurized air source is configured to supply a flow of pressurized air at a first temperature. The aerodynamic resonator includes an inlet nozzle, a resonance tube, and an outlet port. The aerodynamic resonator is coupled to receive, via the inlet nozzle, the flow of pressurized air at the first temperature and configured to discharge, via the outlet port, the flow of pressurized air at a second temperature into the at least one flow channel of the component, wherein the second temperature is greater than the first temperature.
1 . An anti-ice/de-ice system, comprising:
a component having at least one flow channel extending therethrough;
a pressurized air source configured to supply a flow of pressurized air at a first temperature; and
an aerodynamic resonator including an inlet nozzle, a resonance tube, and an outlet port, the aerodynamic resonator coupled to receive, via the inlet nozzle, the flow of pressurized air at the first temperature and configured to discharge, via the outlet port, the flow of pressurized air at a second temperature into the at least one flow channel of the component,
wherein the second temperature is greater than the first temperature.
2 . The system of claim 1 , wherein:
the resonance tube includes an open end and a closed end;
the inlet nozzle is coupled to receive the flow of pressurized air at the first temperature and is configured to inject the flow of pressurized air into the open end of the resonance tube;
the resonance tube is configured to create shock wave reflections thereby increasing pressurized air temperature and pressure at the open end of the resonance tube; and
the flow of pressurized air at the second temperature is discharged out the outlet port.
3 . The system of claim 1 , wherein the component comprises a static compressor blade.
4 . The system of claim 1 , wherein:
the component includes an inner surface and an outer surface; and
the inner surface and the at least one flow channel together define an internal flow volume.
5 . The system of claim 4 , wherein the component comprises at least one static compressor blade.
6 . The system of claim 4 , wherein the component comprises an inlet portion of a gas turbine engine nacelle.
7 . The system of claim 4 , wherein the component comprises at least one aircraft control surface.
8 . The system of claim 1 , wherein the aerodynamic resonator is formed integrally with the component.
9 . The system of claim 1 , wherein the aerodynamic resonator is operated in one of a jet regurgitant mode or a jet screech mode.
10 . The system of claim 1 , wherein:
the at least one flow channel includes a flow channel inlet and a flow channel outlet; and
the system further comprises a valve disposed downstream of the flow channel outlet, the valve moveable between a closed position, in which the flow of pressurized air at the second temperature cannot flow through the at least one flow channel and out the flow channel outlet, and an open position, in which the flow of pressurized air at the second temperature can flow through the at least one flow channel and out the flow channel outlet.
11 . An aircraft anti-ice/de-ice system, comprising:
an aircraft component having at least one flow channel extending therethrough;
a pressurized air source disposed on or within the aircraft, the pressurized air source configured to supply a flow of pressurized air at a first temperature; and
an aerodynamic resonator disposed on or within the aircraft, the aerodynamic resonator including an inlet nozzle, a resonance tube, and an outlet port, the aerodynamic resonator coupled to receive, via the inlet nozzle, the flow of pressurized air at the first temperature and configured to discharge, via the outlet port, the flow of pressurized air at a second temperature into the at least one flow channel of the component,
wherein the second temperature is greater than the first temperature.
12 . The system of claim 11 , wherein:
the resonance tube includes an open end and a closed end;
the inlet nozzle is coupled to receive the flow of pressurized air at the first temperature and is configured to inject the flow of pressurized air into the open end of the resonance tube;
the resonance tube is configured to create shock wave reflections thereby increasing pressurized air temperature and pressure at the open end of the resonance tube; and
the flow of pressurized air at the second temperature is discharged out the outlet port.
13 . The system of claim 11 , wherein the aircraft component comprises one or more of a static compressor blade, an inlet portion of a gas turbine engine nacelle, and an aircraft control surface.
14 . The system of claim 11 , wherein the aerodynamic resonator is formed integrally with the aircraft component.
15 . The system of claim 11 , wherein:
the at least one flow channel includes a flow channel inlet and a flow channel outlet; and
the system further comprises a valve disposed downstream of the flow channel outlet, the valve moveable between a closed position, in which the flow of pressurized air at the second temperature cannot flow through the at least one flow channel and out the flow channel outlet, and an open position, in which the flow of pressurized air at the second temperature can flow through the at least one flow channel and out the flow channel outlet.
16 . An anti-ice/de-ice system, comprising:
a component including a pressurized air inlet, a pressurized air outlet, and having a plurality of cavities formed therein, each cavity having at least a cavity inlet port and a cavity outlet port;
a pressurized air source configured to supply a flow of pressurized air at a first temperature to each of the cavities via the pressurized air inlet; and
a plurality of aerodynamic resonators formed integrally with the component, each aerodynamic resonator associated with a different one of the plurality of cavities and including an inlet nozzle, a resonance tube, and an outlet port, each inlet nozzle in fluid communication with the cavity outlet port of its associated cavity, each outlet port in fluid communication with the pressurized air outlet, each aerodynamic resonator coupled to receive, via its inlet nozzle, the flow of pressurized air at the first temperature from its associated cavity outlet port and configured to discharge, via the outlet port, the flow of pressurized air at a second temperature out the pressurized air outlet,
wherein the second temperature is greater than the first temperature.
17 . The system of claim 16 , further comprising:
a valve disposed downstream of, and in fluid communication with, the pressurized air outlet, the valve moveable between a closed position, in which the flow of pressurized air at the second temperature cannot flow out of the pressurized air outlet, and an open position, in which the flow of pressurized air at the second temperature can flow out of the pressurized air outlet.
18 . The system of claim 16 , wherein:
each resonance tube includes an open end and a closed end;
each inlet nozzle is coupled to receive the flow of pressurized air at the first temperature and is configured to inject the flow of pressurized air into the open end of the resonance tube;
each resonance tube is configured to create shock wave reflections thereby increasing pressurized air temperature and pressure at the open end of the resonance tube; and
the flow of pressurized air at the second temperature is discharged out the outlet port.
19 . The system of claim 16 , wherein the aircraft component comprises one or more of a static compressor blade, an inlet portion of a gas turbine engine nacelle, and an aircraft control surface.
20 . The system of claim 16 , wherein the aerodynamic resonator is formed integrally with the aircraft component.