Airfoil with variable profile responsive to thermal conditions

Patent metadata

Field	Value
Publication number	US-9650898-B2
Application number	US-201213728075-A
Country	US
Kind code	B2
Filing date	Dec 27, 2012
Priority date	Dec 27, 2012
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.

First claim

What is claimed is:

1. An airfoil comprising:
an airfoil body including a first section and a second section that differ by coefficient of thermal expansion, the second section being arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions, wherein the first section and the second section are different composition metallic materials, and the first section is a core and the second section is a shell circumscribing the core, and wherein the at least one of the first section and the second section includes a cross-pattern.

2. The airfoil as recited in claim 1 , wherein the first section and the second section are different compositions selected from aluminum, aluminum alloys, titanium, titanium alloys, iron, iron alloys, nickel, nickel alloys, cobalt, cobalt alloys and combinations thereof.

3. The airfoil as recited in claim 1 , wherein the first section and the second section each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body.

4. The airfoil as recited in claim 1 , including a distinct boundary between the first section and the second section.

5. The airfoil as recited in claim 1 , including a compositional gradient boundary between the first section and the second section.

6. The airfoil as recited in claim 1 , wherein the core terminates at an intermediate span between ends of the airfoil body.

7. The airfoil as recited in claim 1 , wherein the core tapers along a span-wise direction of the airfoil body.

8. The airfoil as recited in claim 1 , wherein the shell has a shell coefficient of thermal expansion and the core has a core coefficient of thermal expansion that is higher than the shell coefficient of thermal expansion.

9. The airfoil as recited in claim 1 , wherein the different composition metallic materials are selected from aluminum, aluminum alloys, titanium, titanium alloys, iron, iron alloys, nickel, nickel alloys, cobalt, cobalt alloys, and wherein at least one of the different composition metallic materials is the aluminum or the aluminum alloy.

10. The airfoil as recited in claim 1 , wherein the different composition metallic materials are selected from aluminum, aluminum alloys, titanium, titanium alloys, iron, iron alloys, nickel, nickel alloys, cobalt, cobalt alloys, and wherein at least one of the different composition metallic materials is the cobalt or the cobalt alloy.

11. A turbomachine comprising:
an airfoil including an airfoil body having a first section and a second section that differ by coefficient of thermal expansion, the second section being arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions, wherein the first section and the second section are different composition metallic materials, and the first section is a core and the second section is a shell circumscribing the core.

12. The turbomachine as recited in claim 11 , further including a turbine section that includes the airfoil.

13. The airfoil as recited in claim 12 , further including a compressor section and a combustor in fluid communication with the compressor section, the turbine section in fluid communication with the combustor.

14. A method of controlling an airfoil profile, the method comprising:
controlling a profile of an airfoil body in response to varying thermal conditions by thermomechanically juxtaposing a first section and a second section of the airfoil body that differ by coefficient of thermal expansion, wherein the first section and the second section are different composition metallic materials, and the first section is a core and the second section is a shell circumscribing the core, and wherein the at least one of the first section and the second section includes a cross-pattern.

Assignees

• Hayford Richard K
• Lutjen Paul M
• United Technologies Corp

Inventors

• Hayford Richard K
• Lutjen Paul M

Classifications

• F05D2300/50212

  dissimilar · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/28 Primary

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• F01D5/148 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title