Fan blade damping device

Patent metadata

Field	Value
Publication number	US-10301948-B2
Application number	US-201314768586-A
Country	US
Kind code	B2
Filing date	Dec 16, 2013
Priority date	Mar 14, 2013
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

An airfoil for a gas turbine engine and method of manufacture of the airfoil are disclosed. The airfoil may comprise a first side extending axially from a leading edge to a trailing edge and extending radially from a base to a tip, a second side opposite to the first side, a pocket disposed in the first side, a filler disposed in the pocket, and a preloaded spring disposed within the filler.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, comprising:
a first side extending axially from a leading edge to a trailing edge and extending radially from a base to a tip;
a second side opposite to the first side;
a pocket disposed in the first side;
a filler with a preloaded spring disposed therein and disposed in the pocket, wherein the preloaded spring is embedded in the filler when the filler is being disposed in the pocket, wherein the preloaded spring exerts a force within the pocket for resisting flutter of the airfoil and for damping vibratory response of the airfoil.

2. The airfoil of claim 1 , wherein the filler surrounds and encapsulates the preloaded spring, and is formed to fill the pocket.

3. The airfoil of claim 2 , wherein the filler dampens a vibratory response of the airfoil, prevents decompression of the preloaded spring, imparts force exerted from the preloaded spring to the airfoil, and prevents contact of the preloaded spring with the pocket.

4. The airfoil of claim 1 , wherein the filler is bonded to the pocket of the first side, and the second side is bonded to the first side and the filler.

5. The airfoil of claim 1 , wherein the preloaded spring and the filler are configured to change an inherent frequency of the airfoil to a predetermined frequency outside a range of resonant frequencies of the airfoil.

6. The airfoil of claim 5 , wherein at least one of a composition of the filler, thickness of the filler, durometer of the filler, thickness of the preloaded spring, preload of the preloaded spring, stiffness of the preloaded spring, and heat treatment of the preloaded spring is configured to change the inherent frequency of the fan blade to the predetermined frequency.

7. The airfoil of claim 1 , wherein the preloaded spring includes at least one gusset for increasing stiffness of the preloaded spring.

8. The airfoil of claim 7 , wherein at least one of a width, depth, radii, thickness, and heat treatment of the at least one gusset is configured to change the inherent frequency of the airfoil to a predetermined frequency outside a range of resonant frequencies of the airfoil.

9. The airfoil of claim 1 , wherein the preloaded spring includes at least one hole to allow attachment of the filler to the preloaded spring.

10. The airfoil of claim 1 , wherein the preloaded spring is composed of a sheet of spring steel having an outline similar to an outline of the pocket.

11. The airfoil of claim 1 , wherein the filler is composed of an elastomeric material.

12. A method for manufacturing an airfoil of a gas turbine engine, comprising:
providing a spring with a predetermined load;
embedding the spring within a filler;
bonding the filler to a cavity of a first side of the airfoil;
bonding a second side of the airfoil to the filler and the first side of the airfoil, wherein the spring is embedded in the filler prior to the bonding steps; and
wherein the spring exerts a force within the cavity to resist flutter of the airfoil and to dampen a vibratory response of the airfoil.

13. The method of claim 12 , further comprising configuring at least one of the predetermined load of the spring, thickness of the spring, stiffness of the spring, heat treatment of the spring, composition of the filler, thickness of the filler, and durometer of the filler, to dampen a frequency of the airfoil and reduce risk of high and low cycle fatigue.

14. The method of claim 12 , further comprising cutting a contour of the spring from a sheet of spring steel to correspond to a contour of the cavity.

15. The method of claim 14 , further comprising providing holes in the spring to allow molding of the filler therethrough.

16. The method of claim 12 , further comprising forming at least one gusset in the spring.

17. The method of claim 12 , further comprising molding the filler to fill the cavity of the first side of the airfoil.

Assignees

• United Technologies Corp

Inventors

• Wilber John E

Classifications

• F05D2230/40

  Heat treatment · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title