Airfoil with thickened root and fan and engine incorporating same

Patent metadata

Field	Value
Publication number	US-10968747-B2
Application number	US-201314761738-A
Country	US
Kind code	B2
Filing date	Dec 18, 2013
Priority date	Mar 15, 2013
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.

First claim

What is claimed is:

1. An airfoil, comprising:
a platform; and
a blade extending from the platform, the blade having a root and a tip each radially outward from the platform, the root being located between the tip and the platform and the blade has a radial height from the platform to the tip;
wherein the root has a fillet where the blade joins the platform of the airfoil, the fillet having a width that varies along an axial length of the blade, and a cross-sectional thickness of the blade at the root is greater than a cross-sectional thickness of the blade along at least 75% of the radial height of the blade as defined from the tip to the platform; and
wherein the blade includes a leading edge, a trailing edge and a central portion, the central portion between the leading edge and the trailing edge, the leading edge interacting with incoming airflow before other surfaces of the blade, the trailing edge interacting with outgoing airflow, and the width of the fillet at the leading edge and the trailing edge of the blade is less than the width of the fillet at the central portion.

2. The airfoil of claim 1 , wherein the cross-sectional thickness of the root of the blade is twenty percent greater than a cross-section thickness of the blade along at least 75% of the radial height of the blade.

3. The airfoil of claim 1 , wherein the root of the blade includes about twenty-five percent of the radial height of the blade.

4. The airfoil of claim 1 , further including a transition zone between the tip and the root of the blade.

5. The airfoil of claim 1 , wherein the fillet has an elliptical shape and a height of the fillet is half of a major axis of the fillet and the width is half of a minor axis of the fillet.

6. The airfoil of claim 1 , wherein the central portion extends from the leading edge to the trailing edge.

7. A fan of a gas turbine engine, comprising:
a hub; and
a plurality of airfoils radially extending from the hub, each airfoil having a platform and a blade extending from the platform, the blade having a root and a tip each radially outward from the platform;
wherein the root has a fillet where the blade joins with the platform, the root being located between the tip and the platform and the blade has a radial height from the platform to the tip, wherein a cross-sectional thickness of the blade at the root is greater than a cross-sectional thickness of the blade along at least 75% of the radial height of the blade as defined from the tip to the platform; and
wherein the blade includes a leading edge and a trailing edge, the leading edge interacting with incoming airflow before other surfaces of the blade and the trailing edge interacting with outgoing airflow, and the fillet has a width in an axial direction of the blade at the leading edge and the trailing edge, wherein the width of the fillet at the leading edge and the trailing edge is less than a width of the fillet in an axial direction of the fillet located between the leading edge and the trailing edge.

8. The fan of claim 7 , wherein the cross-sectional thickness of the root of the blade is twenty percent greater than a cross-section thickness of the blade along at least 75% of the radial height of the blade.

9. The fan of claim 7 , wherein the root of the blade is about twenty-five percent of the radial height of the blade.

10. The fan of claim 7 , wherein the airfoil further includes a transition zone between the tip and the root of the blade.

11. The fan of claim 7 , wherein the blade includes a central portion, the central portion extending between the leading and trailing portions.

12. A gas turbine engine, comprising:
a fan including an airfoil having a platform and a blade extending radially outward from the platform, wherein the blade has a root and a tip each radially outward from the platform, the root being located between the tip and the platform and the blade has a radial height from the platform to the tip, wherein a cross-sectional thickness of the blade at the root is greater than a cross-sectional thickness of the blade along at least 75% of the radial height of the blade as defined from the tip to the platform, and the root has a fillet where the blade joins with the platform, wherein the fillet has a circumferential width and the blade has an axial length, the circumferential width of the fillet varying along the axial length of the blade; and
wherein the blade includes a leading edge, a trailing edge and a central portion, the central portion between the leading edge and the trailing edge, the leading edge interacting with incoming airflow before other surfaces of the blade, the trailing edge interacting with outgoing airflow, and the width of the fillet at the leading edge and the trailing edge of the blade is less than the width of the fillet at the central portion;
a compressor downstream from the fan;
a combustor downstream from the compressor; and
a turbine downstream from the combustor.

13. The gas turbine engine of claim 12 , wherein the root of the blade has a thickness about twenty-five percent greater than the tip of the blade.

14. The gas turbine engine of claim 12 , wherein the cross-sectional thickness of the root of the blade is greater than a cross sectional thickness of the blade along at least 75% of the radial height of the blade.

15. The gas turbine engine of claim 12 , wherein the blade further includes a transition zone between the tip and the root of the blade.

16. The airfoil of claim 12 , wherein the central portion extends from the leading edge to the trailing edge.

Assignees

• Raytheon Tech Corp

Inventors

• Gray Eric D
• Florea Razvan Virgil
• Stucky Mark B
• Lin Ray-Sing

Classifications

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2250/71

  curved · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title