Airfoil deicing system
A gas turbine engine includes an airfoil and a deicing system. The airfoil radially extends from a hub towards a case disposed about a central longitudinal axis of the gas turbine engine. The deicing system includes an acoustic driver assembly arranged to apply acoustic energy to the airfoil to excite a predetermined vibratory mode of the airfoil.
1. A deicing system for a gas turbine engine, comprising:
an acoustic driver that is arranged to apply acoustic energy to an airfoil to excite a predetermined vibratory mode of the airfoil, the acoustic driver being spaced apart from the airfoil and secured to an engine structure.
2. The deicing system as in claim 1 , wherein the acoustic driver is disposed aft of the airfoil.
3. The deicing system of claim 1 , wherein the deicing system further comprises: a plurality of openings defined in a hub, the plurality of openings being arranged to receive bleed air from a core engine and direct the bleed air towards a base of the airfoil.
4. A deicing system for a gas turbine engine having a central longitudinal axis, the deicing system comprising:
an acoustic driver that is arranged to apply acoustic energy to an airfoil to excite a predetermined vibratory mode of the airfoil, the acoustic driver being spaced apart from the airfoil; and
a vibration sensor arranged to provide a signal indicative of a vibratory signature of the airfoil, the vibration sensor being disposed on a case of the gas turbine engine that is disposed about the airfoil.
5. The deicing system of claim 4 , wherein the deicing system further comprises:
a controller in communication with the acoustic driver and is arranged to receive the signal.
6. The deicing system of claim 5 , wherein the controller is programmed to, responsive to the signal being indicative of the vibratory signature of the airfoil being greater than a threshold, command the acoustic driver to apply acoustic energy to the airfoil.
7. The deicing system of claim 4 , wherein the acoustic driver is aft of the airfoil.
8. A deicing system for a gas turbine engine having a central longitudinal axis, the deicing system comprising:
an acoustic driver that is arranged to apply acoustic energy to an airfoil to excite a predetermined vibratory mode of the airfoil, the acoustic driver being spaced apart from the airfoil; and
an ice detection sensor disposed on at least one of a case and an engine structure, the ice detection sensor arranged to provide a signal indicative of ice formation on the airfoil.
9. The deicing system of claim 8 , wherein the acoustic driver is disposed on a case that is disposed about the airfoil.
10. The deicing system of claim 8 , wherein the deicing system further comprises:
a controller in communication with the acoustic driver and arranged to receive the signal.
11. The deicing system of claim 10 , wherein the controller is programmed to, responsive to the signal being indicative of ice formation on the airfoil, command the acoustic driver to apply acoustic energy to the airfoil.
12. A deicing system for a gas turbine engine having a central longitudinal axis, the deicing system comprising:
an acoustic driver that is arranged to apply acoustic energy to an airfoil to excite a predetermined vibratory mode of the airfoil, the acoustic driver being spaced apart from the airfoil; and
a controller in communication with the acoustic driver, wherein the controller is programmed to, responsive to a request to de-ice the airfoil, command the acoustic driver to apply acoustic energy to the airfoil.
13. A gas turbine engine, comprising:
an airfoil radially extending from a hub towards a case disposed about a central longitudinal axis of the gas turbine engine; and
a deicing system, comprising:
an acoustic driver assembly arranged to apply acoustic energy to the airfoil to excite a predetermined vibratory mode of the airfoil.
14. The gas turbine engine of claim 13 , wherein the acoustic driver assembly comprises:
a first acoustic driver extending through the case and disposed proximate at least one of a leading edge and a tip of the airfoil.
15. The gas turbine engine of claim 14 , wherein the acoustic driver assembly comprises:
a second acoustic driver spaced apart from the first acoustic driver, the second acoustic driver extending through the case and disposed proximate at least one of a trailing edge and a tip of the airfoil.
16. The gas turbine engine of claim 15 , wherein the deicing system further comprises:
a vibration sensor arranged to provide a signal indicative of a vibratory signature of the airfoil; and
a controller in communication with at least one of the first acoustic driver and the second acoustic driver and is arranged to receive the signal, the controller programmed to, responsive to the signal being indicative of the vibratory signature of the airfoil being greater than a threshold, command at least one of the first acoustic driver and the second acoustic driver to apply acoustic energy to the airfoil.
17. The gas turbine engine of claim 15 , wherein the deicing system further comprises:
a temperature sensor arranged to provide a signal indicative of a temperature proximate the airfoil; and
a controller in communication with at least one of the first acoustic driver and the second acoustic driver and is arranged to receive the signal, the controller programmed to, responsive to the signal being indicative of a temperature less than a threshold, command at least one of the first acoustic driver and the second acoustic driver to apply acoustic energy to the airfoil.
18. The gas turbine engine of claim 15 , wherein the deicing system further comprises:
an ice detection sensor arranged to provide a signal indicative of ice formation on the airfoil; and
a controller in communication with at least one of the first acoustic driver and the second acoustic driver and is arranged to receive the signal, the controller programmed to, responsive to the signal being indicative of ice formation on the airfoil, command at least one of the first acoustic driver and the second acoustic driver to apply acoustic energy to the airfoil.
19. A method of deicing an airfoil of a gas turbine engine, comprising:
applying acoustic energy to an airfoil via an acoustic driver that is spaced apart from the airfoil, wherein the acoustic energy excites a predetermined vibratory mode of the airfoil, wherein the acoustic energy is applied to the airfoil in response to a vibratory signature of the airfoil that is greater than a threshold.