Frequency tuned hybrid blade

• US 5,947,688 A
• Filed: 12/22/1997
• Issued: 09/07/1999
• Est. Priority Date: 12/22/1997
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Schilling, Jan C., Cornell, Jay L., Stevenson, Joseph T.
• Primary Examiner(s): Ryznic, John E.
• Application Number:
  US08/995,975
• Time in Patent Office: 624 Days
• Field of Search: 416/224, 416/229 A, 416/229 R, 416/230, 416/232, 416/233, 416/241 A, 416/241 B
• US Class Current: 416/233
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.

Claims

1. A gas turbine engine fan blade comprising:

a metal airfoil having first and second opposite sides extending radially between a root and a tip, and axially between a leading edge and a trailing edge for pressurizing air channeled thereover;

said airfoil further including a plurality of pockets disposed in said first side and separated by corresponding ribs;

a filler bonded in said pockets, and being coextensive with said airfoil first side; and

said ribs include radial and diagonal ribs respectively intersecting solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration;

wherein said diagonal rib extends from said leading edge to said trailing edge and is integrally joined to said radial rib therebetween.

2. A blade according to claim 1 wherein said airfoil twists from said root to said tip, and said diagonal rib is correspondingly helical.

3. A blade according to claim 2 further comprising:

a first one of said diagonal ribs intersecting said radial rib to define a pair of root pockets spaced radially outwardly from said airfoil root; and

said airfoil has a closed root section between said root pockets and said root for selectively increasing both bending and torsional stiffness.

4. A blade according to claim 3 further comprising a second one of said diagonal ribs spaced radially above said first diagonal rib and intersecting said airfoil tip adjacent one of said leading and trailing edges.

5. A blade according to claim 4 wherein said first and second diagonal ribs are non-parallel.

6. A blade according to claim 5 wherein said first and second diagonal ribs converge from said leading edge toward said trailing edge.

7. A blade according to claim 6 wherein said radial rib and said first and second diagonal ribs define a plurality of mid-span pockets therebetween, and further comprising a bridging rib spaced radially between said first and second diagonal ribs, and extending axially between said leading edge and said radial rib to stiffen said leading edge against loading thereon.

8. A blade according to claim 4 wherein said filler is elastomeric for damping vibration of said airfoil.

9. A blade according to claim 4 further comprising:

a shank joined integrally with said airfoil root; and

a dovetail joined integrally with said shank for mounting said blade to a rotor disk.

10. A blade according to claim 9 further comprising a plurality of bores extending radially through said shank and airfoil root section to below said root pockets.

11. A blade according to claim 4 wherein said first side is generally concave.

12. A blade according to claim 4 wherein said ribs include solely said radial and diagonal ribs.