Hollow fan blade with extended wing sheath

Patent metadata

Field	Value
Publication number	US-9995152-B2
Application number	US-201314770633-A
Country	US
Kind code	B2
Filing date	Dec 16, 2013
Priority date	Mar 15, 2013
Publication date	Jun 12, 2018
Grant date	Jun 12, 2018

Abstract

A fan blade for a turbomachinery fan and methods for fabricating a fan blade for a turbomachinery fan are disclosed. The fan blade for a turbomachinery fan includes an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side. The fan blade includes a sheath including a solid portion that covers the leading edge of the airfoil, a first wing attached to the suction side of the airfoil, and a second wing attached to the pressure side of the airfoil. Construction of the fan blade includes one or more hollow cavities between the suction side and the pressure side of the airfoil.

First claim

What is claimed is:

1. A fan blade for a gas turbine engine, the fan blade comprising:
an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side;
a sheath comprising a solid portion that covers the leading edge of the airfoil, wherein at least one of a first wing and a second wing of the sheath extends over at least 35% of the airfoil in a chordwise direction in a region of the airfoil near the tip of the airfoil, and wherein at least one of the first wing and the second wing are tapered; and
a blade body between the suction side and the pressure side of the airfoil, wherein the blade body defines a cavity and wherein the cavity is located in a portion of the airfoil covered by the sheath.

2. The fan blade of claim 1 , wherein the cavity is filled with a material having a lighter density than the airfoil.

3. The fan blade of claim 2 , wherein the material having a lighter density than the airfoil is a hybrid metallic substance.

4. The fan blade of claim 1 , wherein the airfoil is constructed from aluminum.

5. The fan blade of claim 4 , wherein the cavity is filled with a hybrid metallic substance having a lower density than aluminum.

6. The fan blade of claim 1 , wherein the sheath is titanium.

7. The fan blade of claim 1 , wherein the first wing is attached to the suction side of the airfoil; and
the second wing is attached to the pressure side of the airfoil.

8. The fan blade of claim 1 , wherein the first wing and the second wing of the sheath are secured to the airfoil by bonding.

9. A method of fabricating a blade for a gas turbine engine, the blade having an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side, and a blade body between the suction side and the pressure side, the method comprising:
forming a sheath over the airfoil, the sheath having a solid portion that covers the leading edge of the airfoil, wherein at least one of a first wing and a second wing of the sheath extends over at least 35% of the airfoil in a chordwise direction in a region of the airfoil near the tip of the airfoil, and wherein at least one of the first wing and the second wing are tapered;
forming one or more hollow cavities between the suction side and the pressure side of the airfoil; and
wherein at least one of the one or more hollow cavities are located in a portion of the airfoil covered by the sheath.

10. The method of claim 9 , further comprising filling the one or more hollow cavities with a material having a lighter density than the airfoil.

11. The method of claim 9 , further comprising filling the one or more hollow cavities with a hybrid metallic substance.

12. The method of claim 9 , further comprising constructing the airfoil from aluminum.

13. A gas turbine engine, comprising:
a fan, the fan comprising at least one fan blade, the at least one fan blade comprising:
an airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side;
a sheath comprising a solid portion that covers the leading edge of the airfoil, wherein at least one of a first wing and a second wing of the sheath extends over at least 35% of the airfoil in a chordwise direction in a region of the airfoil near the tip of the airfoil, wherein at least one of the first wing and the second wing are tapered; and
a blade body between the suction side and the pressure side of the airfoil, wherein the blade body defines a cavity and wherein the cavity is located in a portion of the airfoil covered by the sheath;

a compressor section downstream of the fan;
a combustor section downstream of the compressor section; and
a turbine section downstream of the combustor section.

14. The gas turbine engine of claim 13 , wherein the cavity is filled with a material having a lighter density than the airfoil.

Assignees

• United Technologies Corp

Inventors

• Mccomb Patrick James

Classifications

• F05D2300/121

  Aluminium · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2220/32

  in gas turbines · CPC title