Fan blade with internal shear-thickening fluid damping

Patent metadata

Field	Value
Publication number	US-11746659-B2
Application number	US-202117561617-A
Country	US
Kind code	B2
Filing date	Dec 23, 2021
Priority date	Dec 23, 2021
Publication date	Sep 5, 2023
Grant date	Sep 5, 2023

Abstract

An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a shear-thickening fluid disposed in the cavity. A viscosity of the shear-thickening fluid increases in response to the airfoil experiencing an aeromechanic response or vibrations such that the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.

First claim

What is claimed is:

1. An airfoil for use in a gas turbine engine, the airfoil comprising
an airfoil body extending radially outwardly relative to an axis and configured to interact with gases surrounding the airfoil body, the airfoil body having a leading edge, a trailing edge opposite the leading edge, a pressure side, and a suction side opposite the pressure side, the airfoil body formed to define a cavity within the airfoil body, the cavity being defined by a radially outer top surface, a radially inner bottom surface, a first inner side surface, a second inner side surface, a pressure side inner surface, and a suction side inner surface, the airfoil body including a shear-thickening fluid disposed within the cavity, wherein a viscosity of the shear-thickening fluid increases in response to the airfoil experiencing at least one of an aeromechanic response and vibrations during use of the airfoil, and
at least one obstructing member arranged within the cavity and fixed to the airfoil body to obstruct movement of the shear-thickening fluid within the cavity in response to the viscosity of the shear-thickening fluid increasing so as to dampen the vibrations of the airfoil and reduce negative effects of a dynamic response of the airfoil,
wherein the at least one obstructing member includes a plurality of pegs that each extend from the pressure side inner surface to the suction side inner surface of the cavity and contact the pressure and suction side inner surfaces.

2. The airfoil of claim 1 , wherein the plurality of pegs includes at least two rows of pegs, each row including at least two pegs, wherein each row of pegs of the at least two rows of pegs extends from the leading edge to the trailing edge in a direction generally axially relative to the axis, wherein each row of pegs of the at least two rows of pegs is spaced apart from an adjacent row of pegs in a radially direction.

3. The airfoil of claim 1 , wherein the airfoil body includes an airfoil root and an airfoil tip spaced apart radially outward from the airfoil root, and wherein the radially outer top surface of the cavity is located adjacent to the airfoil tip.

4. The airfoil of claim 3 , wherein the cavity is arranged radially outwardly of a halfway point of a radial extent of the airfoil body.

5. A rotor assembly for use in a gas turbine engine, the rotor assembly comprising
a wheel arranged circumferentially about an axis, and
a first airfoil extending radially outwardly from the wheel relative to the axis and configured to interact with gases surrounding the first airfoil, the first airfoil including
a first airfoil body extending radially outwardly relative to an axis and configured to interact with gases surrounding the first airfoil body, the first airfoil body having a leading edge, a trailing edge opposite the leading edge, a pressure side, and a suction side opposite the pressure side, the first airfoil body formed to define a first cavity within the first airfoil body, wherein the first cavity is defined by a radially outer top surface, a radially inner bottom surface, a first inner side surface, a second inner side surface, a pressure side surface, and a suction side surface, the first airfoil body including a first shear-thickening fluid disposed within the first cavity, wherein a viscosity of the first shear-thickening fluid increases in response to the first airfoil experiencing at least one of an aeromechanic response and vibrations during use of the airfoil, and
at least one first obstructing member arranged within the first cavity and configured to obstruct movement of the first shear-thickening fluid within the first cavity in response to the viscosity of the first shear-thickening fluid increasing so as to dampen the vibrations of the first airfoil and reduce negative effects of a dynamic response of the first airfoil,
wherein the at least one first obstructing member includes a plurality of pegs that each extend from the pressure side inner surface to the suction side inner surface of the cavity and contact the pressure and suction side inner surfaces.

6. A method comprising
providing an airfoil body having a leading edge, a trailing edge opposite the leading edge, a pressure side, and a suction side opposite the pressure side,
forming a cavity within the airfoil body,
filling the cavity with a shear-thickening fluid, wherein a viscosity of the shear-thickening fluid increases in response to the airfoil experiencing at least one of an aeromechanic response and vibrations during use of the airfoil, and
arranging at least one obstructing member within the cavity that is configured to obstruct movement of the shear-thickening fluid within the cavity in response to the viscosity of the shear-thickening fluid increasing so as to dampen the vibrations of the airfoil and reduce negative effects of a dynamic response of the airfoil,
wherein the at least one obstructing member includes a plurality of pegs that each extend from a first side inner surface of the cavity to a second side inner surface of the cavity opposite the first side inner surface and contact the first and second side inner surfaces.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Heeter Robert W
• Molnar Jr Daniel E
• Hall Christopher D

Classifications

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · 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

• F05D2300/501

  Elasticity · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title