Piezoelectric vibratory control for static engine components

Patent metadata

Field	Value
Publication number	US-10697320-B2
Application number	US-201815867309-A
Country	US
Kind code	B2
Filing date	Jan 10, 2018
Priority date	Jan 20, 2017
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.

First claim

What is claimed is:

1. A gas turbine engine assembly comprising
a wheel assembly having a plurality of blades arranged around a central axis of the gas turbine engine assembly and the wheel assembly configured to rotate about the central axis during use of the gas turbine engine assembly,
a compressor case arranged circumferentially around the plurality of blades included in the wheel assembly, and
a vibration-dampening system coupled to the compressor case to dampen vibration of the compressor case during use of the gas turbine engine assembly and the vibration-dampening system including a first piezoelectric element coupled to the compressor case, a second piezoelectric element coupled to the compressor case, and a circuit coupled to the first piezoelectric element and the second piezoelectric element,
wherein the second piezoelectric element is vibrated by the gas turbine engine assembly at a predetermined frequency during operation of the gas turbine engine assembly, and the first piezoelectric element is configured to generate an electric signal in response to being energized by the vibration of the compressor case during use of the gas turbine engine assembly, the circuit is configured to receive the electric signal, change the phase of the electric signal received from the first piezoelectric element so that the phase of the electric signal transmitted to the second piezoelectric element causes the second piezoelectric element to move in a destructive pattern relative to the predetermined frequency to cause the vibration of the compressor case to be dampened during use of the gas turbine engine.

2. The gas turbine engine assembly of claim 1 , wherein the circuit is configured to change the phase of the electric signal received from the first piezoelectric element to be about 180 degrees apart from a phase of the predetermined frequency.

3. The gas turbine engine assembly of claim 1 , wherein the circuit is configured to determine the predetermined frequency.

4. The gas turbine engine assembly of claim 1 , wherein the compressor case includes an outer housing that extends at least partway about the central axis and a plurality of vanes that extend radially between the outer housing and the central axis and the first piezoelectric element is aligned axially with the plurality of vanes.

5. The gas turbine engine assembly of claim 1 , wherein the second piezoelectric element is spaced apart circumferentially from the first piezoelectric element.

6. The gas turbine engine assembly of claim 5 , wherein the second piezoelectric element is aligned axially with the first piezoelectric element.

7. The gas turbine engine assembly of claim 1 , wherein the second piezoelectric element is spaced apart axially from the first piezoelectric element.

8. The gas turbine engine assembly of claim 1 , wherein the vibration-dampening system further includes an electric system, the circuit is coupled to the electric system, and the electric system is powered by at least a portion of the electric signal generated by the first piezoelectric element.

9. The gas turbine engine assembly of claim 8 , wherein the electric system includes a resistive heater.

10. A gas turbine engine assembly comprising
a first component configured to rotate about a central axis of the gas turbine engine assembly,
a second component located adjacent the first component and configured to remain fixed relative to the central axis, and
a vibration-dampening system including a first piezoelectric element and a second piezoelectric element and the first piezoelectric element and the second piezo electric element are coupled to the second component and energized by vibration of the second component during use of the gas turbine engine assembly,
wherein the vibration-dampening system further includes a circuit connected to the first piezoelectric element and the second piezoelectric element, the first piezoelectric element generates a first electric signal, the second piezoelectric element generates a second electric signal, and the circuit is configured to receive the first electric signal and the second electric signal, change a phase of the first electric signal and the second electric signal, transmit the first electric signal to the second piezoelectric element, and transmit the second electric signal to the first piezoelectric element after changing the phase of the first electric signal and the second electric signal.

11. The gas turbine engine assembly of claim 10 , wherein the vibration-dampening system further includes an electric heater connected to the first piezoelectric element and powered by the first piezoelectric element in response to the first piezoelectric element being energized.

12. A gas turbine engine assembly comprising
a first component configured to rotate about a central axis of the gas turbine engine assembly,
a second component located adjacent the first component and configured to remain fixed relative to the central axis, a vibration-dampening system including a first piezoelectric element and a second piezoelectric element and the first piezoelectric element and the second piezo electric element are coupled to the second component and energized by vibration of the second component during use of the gas turbine engine assembly, and
a circuit connected to the first piezoelectric element and the second piezoelectric element, the second component includes a first vane and a second vane, the first piezoelectric element is aligned axially and circumferentially with the first vane, the second piezoelectric element is aligned axially and circumferentially with the second vane, the first vane vibrates with a first phase during operation of the gas turbine engine assembly, the second vane vibrates with a second phase during operation of the gas turbine engine assembly, and the circuit is configured to receive an electric signal from the first piezoelectric element, change a phase of the electric signal so that the phase is destructive to the vibration of the second vane, and transmit the electric signal to the second piezoelectric element after changing the phase.

Assignees

• Rolls Royce Corp

Inventors

• Fulayter Roy D
• Meyer Michael G

Classifications

• F01D25/04 Primary

  Antivibration arrangements · CPC title

• G10K2210/1281

  Aircraft, e.g. spacecraft, airplane or helicopter · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2260/962

  by means of "anti-noise" · CPC title

• G10K11/17857

  Geometric disposition, e.g. placement of microphones · CPC title