Fan blade tall dovetail for individually bladed rotors

Patent metadata

Field	Value
Publication number	US-9828864-B2
Application number	US-201314429029-A
Country	US
Kind code	B2
Filing date	Mar 15, 2013
Priority date	Sep 20, 2012
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

First claim

The invention claimed is:

1. A fan blade for a gas turbine engine comprising:
an airfoil defining a pressure and suction side; and
a neck supporting the airfoil and interconnected to a dovetail by opposing radii, the dovetail including a bearing surface tangent to one of the radii at a tangent point, wherein the dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck, and a first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 and 2.90, wherein the neck includes a neck width, and a second ratio of the neck width to the vertical bearing surface height is in a range of 0.95 to 1.18.

2. The fan blade according to claim 1 , wherein the first ratio is in a range of 2.35 to 2.70.

3. The fan blade according to claim 2 , wherein the first ratio is about 2.40.

4. The fan blade according to claim 1 , wherein the second ratio is in a range of about 1.10.

5. The fan blade according to claim 1 , wherein the vertical bearing height is in the range of 0.675 inch to 0.775 inch.

6. A fan section of a gas turbine engine comprising:
a fan rotor including a slot having a load surface;
an airfoil defining a pressure and suction side; and
a neck supporting the airfoil and interconnected to a dovetail by opposing radii, the dovetail received in the slot, the dovetail including a bearing surface tangent to one of the radii at a tangent point, wherein the dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck, and a first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 to 2.90, wherein the neck includes a neck width, and a second ratio of the neck width to the vertical bearing surface height is in a range of 0.95 to 1.18.

7. The fan section according to claim 6 , wherein the bearing surface is configured to react against the load surface during engine operation, and a spacer provided between the bottom and the slot.

8. The fan section according to claim 6 , comprising a fan radius, and a third ratio of the fan radius to the vertical bearing surface height is in a range of 30 to 44.

9. The fan section according to claim 8 , wherein the third ratio is about 39.

10. The fan section according to claim 6 , wherein the vertical bearing height is in the range of 0.675 inch to 0.775 inch.

11. A gas turbine engine comprising:
a fan section including a plurality of fan blades mounted to a fan rotor that is rotatable about an axis;
a compressor section;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor;
a fan drive gear system module coupled to the turbine section for rotating the fan about the axis; and
wherein a neck supports the fan blades and is interconnected to a dovetail by opposing radii, the dovetail received by the fan rotor, the dovetail including a bearing surface tangent to one of the radii at a tangent point, wherein the dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck, and a first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 to 2.90, wherein the neck includes a neck width, and a second ratio of the neck width to the vertical bearing surface height is in a range of 0.95 to 1.18.

12. The gas turbine engine according to claim 11 , comprising a fan radius, and a third ratio of the fan radius to the vertical bearing surface height is in a range of 30 to 44.

Assignees

• United Technologies Corp
• Whitehurst Sean A
• Mccomb Patrick James
• Drozdenko Lee

Inventors

• Whitehurst Sean A
• Mccomb Patrick James
• Drozdenko Lee

Classifications

• F05D2270/114

  by limiting mechanical stresses · CPC title

• F01D5/28

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

• F01D5/3092

  Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence) · CPC title

• F02C3/04

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

• F05D2250/70

  Shape · CPC title