Unshrouded blading for high bypass turbofan engines

• US 5,490,764 A
• Filed: 05/23/1994
• Issued: 02/13/1996
• Est. Priority Date: 05/23/1994
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Schilling, Jan C.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): LARSON, JAMES
• Application Number:
  US08/257,602
• Time in Patent Office: 631 Days
• Field of Search: 416/219 R, 416/229 A, 416/230, 416/232, 416/239, 416/241 R, 416/241 B, 416/500
• US Class Current: 416/239
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Metal alloy fan blades reinforced with a metal matrix composite for enhancing stiffness of the fan blades without a significant weight penalty, and which are suitable for use in high bypass turbofan engines. The metal matrix composite is bonded to each fan blade near its root so as to increase stiffness and thereby provide frequency and stability control to the fan blades. As a result, a lower engine weight can be realized by using more fan blades without the need for a part span shroud.

Claims

1. A metal alloy fan blade for a gas turbine engine, the metal alloy fan

blade comprising:

a blade root;

a blade tip oppositely disposed from the blade root; and

a reinforcing material bonded to a surface of the metal alloy fan blade at the blade root so as to be remote from the blade tip, the reinforcing material being lo provided in a quantity and thickness so as to sufficiently stiffen the metal alloy fan blade and thereby provide frequency and stability control to the fan blade;

whereby the reinforcing material sufficiently stiffens the metal alloy fan blade so as to make unnecessary the use of a part span shroud.

2. A metal alloy fan blade as recited in claim 1 wherein the reinforcing material is a metal matrix composite material.

3. A metal alloy fan blade as recited in claim 1 wherein the reinforcing material is a titanium-silicon carbide metal matrix composite material.

4. A metal alloy fan blade as recited in claim 1 wherein the reinforcing material is excluded from regions of the fan blade which are required to be resistant to foreign object damage.

5. A metal alloy fan blade as recited in claim 1 wherein the reinforcing material is limited to the lower third of the metal alloy fan blade adjacent to the blade root.

6. A metal alloy fan blade as recited in claim 1 wherein the thickness of the reinforcing material is about 10 to about 25 percent of the thickness of the metal alloy fan blade.

7. A metal alloy fan blade as recited in claim 1 wherein the metal alloy fan blade is formed from a titanium alloy.

8. A metal alloy fan blade as recited in claim 1 wherein the metal alloy fan blade is hollow.

9. A metal alloy fan blade as recited in claim 1 wherein the reinforcing material is diffusion bonded to the metal alloy fan blade.

10. A fan blade for a gas turbine engine, the fan blade comprising:

a fan blade member having a blade root for securing the fan blade to a hub member and a blade tip oppositely disposed from the blade root, the fan blade member being formed from a titanium alloy; and

a metal matrix composite material bonded to a surface of the fan blade member at the blade root so as to be remote from the blade tip, the metal matrix composite material being provided in a quantity and thickness so as to sufficiently stiffen the fan blade and thereby provide frequency and stability control to the fan blade;

whereby the metal matrix composite material sufficiently stiffens the fan blade so as to increase the fan blade'"'"'s flexural frequency, thereby making unnecessary the use of a part span shroud.

11. A fan blade as recited in claim 10 wherein the metal matrix composite material is a titanium-silicon carbide metal matrix composite material.

12. A fan blade as recited in claim 10 wherein the metal matrix composite is excluded from regions of the fan blade which are required to be resistant to foreign object damage.

13. A fan blade assembly for a gas turbine engine, the fan blade assembly comprising:

a hub member;

a plurality of metal alloy fan blades secured to the hub member, each of the plurality of metal alloy fan blades having a blade root for securing each fan blade to the hub member and a blade tip oppositely disposed from the blade root; and

a metal matrix composite material bonded to a surface of each fan blade at its corresponding blade root so as to be remote from its corresponding blade tip, the metal matrix composite material being provided in a quantity and thickness so as to sufficiently stiffen each fan blade and thereby provide frequency and stability control to each fan blade;

whereby the metal matrix composite material sufficiently stiffens each fan blade so as to make unnecessary the use of a part span shroud.

14. A fan blade assembly as recited in claim 13 wherein each fan blade is formed from a titanium alloy.

15. A fan blade assembly as recited in claim 13 wherein the metal matrix composite material is a titanium-silicon carbide metal matrix composite.

16. A fan blade assembly as recited in claim 13 wherein the metal matrix composite material is excluded from regions of each fan blade which are required to be resistant to foreign object damage.

17. A fan blade assembly as recited in claim 13 wherein the metal matrix composite material is diffusion bonded to the fan blades.

18. A fan blade assembly as recited in claim 13 wherein the metal matrix composite material is metallurgically compatible with titanium.

19. A fan blade assembly as recited in claim 13 wherein the fan blade assembly comprises at least twenty six of the fan blades.