Active airfoil vibration control

Patent metadata

Field	Value
Publication number	US-10822965-B2
Application number	US-201815935186-A
Country	US
Kind code	B2
Filing date	Mar 26, 2018
Priority date	Mar 26, 2018
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil. The apparatus includes an airfoil that has a body and a filler that is embedded within the body. A source for electromagnetic energy is positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil. A physical property of the filler is configured to change between a first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy. The airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

First claim

What is claimed is:

1. An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil, the apparatus comprising:
an airfoil that includes a body, a closed cavity defined in the body, and a filler contained in the cavity, the filler partially filling the cavity to allow the filler to move within the cavity from a first position to a second position when in a first state;
a source for electromagnetic energy positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil;
a physical property of the filler is configured to change between the first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy; and
wherein the airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

2. The apparatus according to claim 1 , wherein the source for electromagnetic energy is mounted in a static portion of the engine.

3. The apparatus according to claim 2 , wherein the airfoil is configured to move relative to the source.

4. The apparatus according to claim 1 , wherein the physical property of the filler that is configured to change is viscosity.

5. The apparatus according to claim 4 , wherein the airfoil characteristic that changes when the physical property of the filler changes is stiffness.

6. The apparatus according to claim 4 , wherein the airfoil characteristic that changes when the physical property of the filler changes is a natural harmonic frequency.

7. The apparatus according to claim 4 , wherein the airfoil characteristic that changes when the physical property of the filler changes is shape.

8. The apparatus according to claim 4 , wherein the airfoil characteristic that changes when the physical property of the filler changes is size.

9. The apparatus according to claim 1 , wherein the filler is formed of a magneto rheological material.

10. A method for changing a physical characteristic of an aircraft engine component utilizing an electromagnetic field, the method comprising the steps of:
generating an electromagnetic field; and
exposing a filler contained in a closed cavity defined in a part of an aircraft engine component to the electromagnetic field, the filler partially filling the closed cavity to allow the filler to move within the cavity from a first position to a second position when in a first state; and
causing a physical property of the filler to change between the first state and a second state.

11. The method according to claim 10 , wherein the step of causing the physical property of the filler to change is preceded by step of providing the electromagnetic field at a predetermined level.

12. The method according to claim 10 , wherein the first state is liquid and the second state is solid.

13. The method according to claim 10 , wherein the physical property of the filler is its viscosity.

14. The method according to claim 10 , further comprising the step of changing a physical characteristic of the aircraft engine component.

15. The method according to claim 14 , wherein the airfoil characteristic that changes when the physical property of the filler changes is stiffness.

16. The method according to claim 14 , wherein the airfoil characteristic that changes when the physical property of the filler changes is a natural harmonic frequency.

17. The method according to claim 14 , wherein the airfoil characteristic that changes when the physical property of the filler changes is shape.

18. The method according to claim 14 , wherein the airfoil characteristic that changes when the physical property of the filler changes is size.

19. An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil, the apparatus comprising:
an airfoil that includes a body, a closed cavity defined in the body, a thin wall disposed in the closed cavity, and a filler contained in the cavity, wherein the thin wall moves in response to changes of the filler as it changes between a first state and a second state such that no air space is present in the cavity;
a source for electromagnetic energy positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil;
a physical property of the filler is configured to change between the first state in the absence of electromagnetic energy and the second state in the presence of electromagnetic energy; and
wherein the airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

20. A method for changing a physical characteristic of an aircraft engine component utilizing an electromagnetic field, the method comprising the steps of:
generating an electromagnetic field; and
exposing a filler contained in a closed cavity defined in a part of an aircraft engine component to the electromagnetic field, the closed cavity having a thin wall defined therein such that the thin wall moves in response to changes of the filler as it changes between a first state and a second state such that no air space is present in the cavity; and
causing a physical property of the filler to change between the first state and the second state.

21. The method according to claim 20 , further comprising the step of changing a physical characteristic of the aircraft engine component.

22. The method according to claim 21 , wherein the airfoil characteristic that changes when the physical property of the filler changes is stiffness.

23. The method according to claim 21 , wherein the airfoil characteristic that changes when the physical property of the filler changes is a natural harmonic frequency.

24. The method according to claim 21 , wherein the airfoil characteristic that changes when the physical property of the filler changes is shape.

25. The method according to claim 21 , wherein the airfoil characteristic that changes when the physical property of the filler changes is size.

Assignees

• Gen Electric

Inventors

• Macmahon Carl L
• Duselis Julie Ann
• Capps Drew Michael
• Choi Yoon Seok
• Mielke Mark Joseph

Classifications

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F05D2270/62

  Electrical actuators · CPC title

• F01D5/26 Primary

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title

• F16F2224/045

  magnetorheological · CPC title

• F05D2300/507

  Magnetic properties · CPC title