Airfoil with variable profile responsive to thermal conditions

Patent metadata

Field	Value
Publication number	US-9752442-B2
Application number	US-201615267186-A
Country	US
Kind code	B2
Filing date	Sep 16, 2016
Priority date	Dec 27, 2012
Publication date	Sep 5, 2017
Grant date	Sep 5, 2017

Abstract

An airfoil includes an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body. 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 in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body, 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 forms a pressure side of the airfoil body and a suction side of the airfoil body, and the second section is disposed on the first section and has a wedge shape that tapers toward a radially inner end of the airfoil body.

2. The airfoil as recited in claim 1 , wherein the first section and the second section are different composition metallic materials.

3. The airfoil as recited in claim 2 , including a compositional gradient boundary between the first section and the second section.

4. 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.

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

6. The airfoil as recited in claim 1 , wherein the first section is a core and the second section is a shell circumscribing the core.

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

8. The airfoil as recited in claim 7 , wherein the first section and the second section are different composition metallic materials.

9. The airfoil as recited in claim 8 , including a compositional gradient boundary between the first section and the second section.

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

11. The airfoil as recited in claim 1 , wherein the second section partially covers at least one of the pressure side or the suction side.

12. A turbomachine comprising:
an airfoil including an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body, 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 forms a pressure side of the airfoil body and a suction side of the airfoil body, and the second section is disposed on the first section and has a wedge shape that tapers toward a radially inner end of the airfoil body.

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

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

15. An airfoil comprising:
an airfoil body including a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body, 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 is a core and the second section is a shell circumscribing the core.

16. The airfoil as recited in claim 15 , wherein the core terminates at an intermediate span between ends of the airfoil body.

17. The airfoil as recited in claim 16 , wherein the first section and the second section are different composition metallic materials.

18. The airfoil as recited in claim 17 , including a compositional gradient boundary between the first section and the second section.

19. The airfoil as recited in claim 16 , wherein the core tapers along a span-wise direction of the airfoil body.

Assignees

• United Technologies Corp

Inventors

• Hayford Richard K
• Lutjen Paul M

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2300/10

  Metals, alloys or intermetallic compounds · CPC title

• F01D5/148

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

• F05D2300/50212

  dissimilar · CPC title

• F01D5/28 Primary

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