Shape memory alloy variable stiffness airfoil

Patent metadata

Field	Value
Publication number	US-10352173-B2
Application number	US-201615058892-A
Country	US
Kind code	B2
Filing date	Mar 2, 2016
Priority date	Mar 2, 2016
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

First claim

What is claimed is:

1. A composite blade for a gas turbine engine, comprising:
an airfoil extending from a leading edge to a trailing edge, the airfoil having a stiffness and a camber, the airfoil having a root and a tip;
a first shape memory alloy (SMA) extending from the leading edge to the trailing edge, the first SMA defining a first direction and mechanically coupled to the airfoil via a first resin; and
a second shape memory alloy (SMA) extending from a first corner defined by a first intersection of the leading edge and the tip to a second corner defined by a second intersection of the trailing edge and the root, the second SMA defining a second direction that is different from the first direction and mechanically coupled to the airfoil via a second resin, wherein the second SMA array is electrically isolated from the first SMA, wherein the camber changes in response to a first phase change of the first SMA and the airfoil twists in response to a second phase change of the second SMA.

2. The composite blade for the gas turbine engine of claim 1 , wherein the composite blade comprises at least one of a carbon fiber composite or a glass fiber composite and the first SMA and the second SMA are configured to be coupled to a current source.

3. The composite blade for the gas turbine engine of claim 2 , wherein the first SMA and the second SMA extend through an inner portion of the airfoil.

4. The composite blade for the gas turbine engine of claim 2 , wherein the first SMA and the second SMA comprise a nickel-titanium alloy configured to change from an austenite phase to a martensite phase in response to a decrease in a current from the current source and configured to change from the martensite phase to the austenite phase in response to an increase in the current from the current source.

5. The composite blade for the gas turbine engine of claim 1 , wherein the first direction is parallel to a fluid flow direction, and the second direction is at least one of an angle to the fluid flow direction or substantially perpendicular to the fluid flow direction.

6. The composite blade for the gas turbine engine of claim 1 , wherein the first SMA and the second SMA extend along an outer surface of the airfoil.

7. The composite blade for the gas turbine engine of claim 1 , wherein the composite blade comprises a laminate, the first SMA and the second SMA being mechanically coupled between a first layer and a second layer of the laminate via the first resin and the second resin, the first resin and the second resin electrically insulating the first SMA and the second SMA.

Assignees

• United Technologies Corp

Inventors

• Prince Troy Shannon
• Bintz Matthew E
• Gendrich Charles P

Classifications

• F05D2300/505

  Shape memory behaviour · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/148 Primary

  Blades with variable camber, e.g. by ejection of fluid · CPC title

• B29D99/0025

  Producing blades or the like, e.g. blades for turbines, propellers, or wings · CPC title

• B29C70/88

  characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced · CPC title