Anti-ice systems for engine airfoils
An anti-ice system for a gas turbine engine may comprise a power generating device and a first thermally conductive applique comprising a first heating circuit. The power generating device may comprise a first component configured to rotate about an axis and generate a current. A first conductive layer may electrically couple the first heating circuit and the first component of the power generating device.
1. An anti-ice system for a gas turbine engine, comprising:
a power generating device comprising:
a first component configured to rotate about an axis and generate a current;
a first magnet located forward of a first surface of the first component, the first surface being oriented in a forward direction; and
a second magnet located aft of a second surface of the first component, the second surface of the first component being oriented away from the first surface and in an aft direction;
a first thermally conductive applique comprising a first heating circuit; and
a first conductive layer electrically coupling the first heating circuit and the first component of the power generating device.
2. The anti-ice system of claim 1 , wherein the first heating circuit comprising a plurality of resistor circuits.
3. The anti-ice system of claim 1 , wherein the first component comprises a Faraday disk.
4. The anti-ice system of claim 3 , wherein a first end of the first conductive layer is coupled to a positive pole of the first component and a second end of the first conductive layer opposite the first end is coupled to a negative pole of the first component.
5. The anti-ice system of claim 1 , further comprising:
a second thermally conductive applique comprising a second heating circuit; and
a second conductive layer electrically coupling the second heating circuit and the first component of the power generating device.
6. The anti-ice system of claim 5 , wherein the first thermally conductive applique is configured to attach to a pressure side of an airfoil of the gas turbine engine, and wherein the second thermally conductive applique is configured to attach a suction side of the airfoil.
7. A gas turbine engine, comprising:
a fan including a rotor disk and a plurality of airfoils located circumferentially about the rotor disk;
a compressor located aft of the fan;
a shaft configured to drive a rotation of the rotor disk and the compressor; and
an anti-ice system thermally coupled to the fan, the anti-ice system comprising:
a power generating device comprising a first component rotationally coupled to the shaft and the rotor disk, a first magnet located over a first surface of the first component, and a second magnet located over a second surface of the first component opposite the first side of the first component,
a first thermally conductive applique bonded to a first airfoil of the fan and comprising a first heating circuit; and
a first conductive layer electrically coupling the first heating circuit and the first component of the power generating device; and
a strut coupling the first magnet and the second magnet to at least one of a vane or a case of the compressor.
8. The gas turbine engine of claim 7 , wherein the anti-ice system further comprises:
a second thermally conductive applique bonded to a second airfoil of the fan and comprising a second heating circuit; and
a second conductive layer electrically coupling the second heating circuit and the first component of the power generating device.
9. The gas turbine engine of claim 8 , wherein
the first magnet is located forward of the first surface of the first component, the first surface of the first component being oriented in a forward direction; and
the second magnet is located aft of the second surface of the first component, the second surface being orient away from the first surface and in an aft direction.
10. The gas turbine engine of claim 7 , wherein the first thermally conductive applique extends over a leading edge of the first airfoil.
11. The gas turbine engine of claim 7 , wherein the first thermally conductive applique comprises a metallic layer covering the first heating circuit.
12. A fan section of a gas turbine engine, comprising:
a rotor disk configured to rotate about an axis of the gas turbine engine;
a plurality of airfoils extending radially outward from the rotor disk;
a shaft configured to drive a rotation of the rotor disk;
an anti-ice system thermally coupled to the plurality of airfoils, the anti-ice system comprising:
a power generating device comprising a piezoelectric device, the piezoelectric device being mounted to a surface of at least one of the rotor disk or the shaft;
a first heating circuit located over a first surface of a first airfoil of the plurality of airfoils; and
a first conductive layer electrically coupling the first heating circuit and the first component of the power generating device.
13. The fan section of claim 12 , wherein the anti-ice system further comprises:
a second heating circuit located over a surface of a second airfoil of the plurality of airfoils; and
a second conductive layer electrically coupling the second heating circuit and the power generating device.
14. The fan section of claim 12 , wherein the anti-ice system further comprises a thermally conductive applique bonded to the first airfoil, the thermally conductive applique comprising the first heating circuit.
15. The fan section of claim 14 , wherein the anti-ice system further comprises:
a second heating circuit located over a second surface of the first airfoil opposite the first surface of the first airfoil; and
a second conductive layer electrically coupling the second heating circuit and the power generating device.
16. The fan section of claim 14 , wherein the first heating circuit is located over a second surface a second surface of the first airfoil opposite the first surface of the first airfoil.