Blade for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9909425-B2
Application number	US-201113285332-A
Country	US
Kind code	B2
Filing date	Oct 31, 2011
Priority date	Oct 31, 2011
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A gas turbine airfoil blade comprises an airfoil having a leading edge and a trailing edge defining fore and aft points of an airfoil chord relative to a flowpath direction. The airfoil extends generally radially from a root to a tip, the root of the airfoil intersecting a platform of the blade. A body of the airfoil is composed of a plurality of airfoil sections stacked along a stacking line extending radially from the platform. A root airfoil section being the one of said airfoil sections intersecting the platform, the trailing edge at the root airfoil section extending to intersect the platform chordwise aft of the trailing edge of the airfoil section immediately radially outwardly adjacent to the root airfoil section.

First claim

What is claimed is:

1. A turbofan fan blade comprising an airfoil having a leading edge and a trailing edge defining fore and aft points of an airfoil chord relative to a flowpath direction, the airfoil extending generally radially from a root to a tip, said leading edge and said trailing edge extending from root to tip, the root of the airfoil intersecting a platform of the blade at a fillet radius, a body of the airfoil composed of a plurality of airfoil sections stacked along a stacking line extending radially from the platform above the fillet radius, a root airfoil section being the one of said plurality of airfoil sections intersecting the fillet radius, said trailing edge shaped at the root airfoil section to intersect the platform chordwise aft of the trailing edge of an airfoil section immediately radially outwardly adjacent to the root airfoil section, a chord length of said airfoil section immediately radially outwardly adjacent to the root airfoil section being less than a chord length of the root airfoil section and less than a chord length of another immediate radially outwardly adjacent airfoil section, a trailing edge concavity formed in the trailing edge adjacent to the fillet radius relative to a remainder of the trailing edge, the concavity being defined at the root airfoil section and said airfoil section immediately radially outwardly adjacent to the root airfoil section, the concavity being nonrepetitive.

2. The turbofan fan blade according to claim 1 , wherein the leading edge of the blade has a forward sweep at the tip.

3. The turbofan fan blade according to claim 1 , wherein a projection of the trailing edge at the root airfoil section intersects the platform at an angle ranging between 65 degrees and 75 degrees relative to an axis of rotation of the blade.

4. The turbofan fan blade according to claim 3 , wherein a projection of the trailing edge at the root airfoil section intersects the platform at an angle of approximately 20 degrees.

5. A turbofan fan comprising a plurality of fan blades, each of the plurality of fan blades having an airfoil circumferentially distributed and projecting radially from a platform, each said airfoil having a leading edge and a trailing edge defining fore and aft points of an airfoil chord relative to a flowpath direction, each said airfoil extending generally radially from a root to a tip, said leading edges and a trailing edges extending from root to tip, the root of each said airfoil intersecting the platform of each fan blade at a fillet radius, a body of each said airfoil composed of a plurality of airfoil sections stacked along a stacking line extending radially from the platform above the fillet radius, a root airfoil section being the one of said plurality of airfoil sections intersecting the fillet radius, said trailing edge shaped at the root airfoil section to intersect the platform chordwise aft of the trailing edge of an airfoil section immediately radially outwardly adjacent to the root airfoil section, a chord length of said airfoil section immediately radially outwardly adjacent to the root airfoil section being less than a chord length of the root airfoil section and less than a chord length of another immediate radially outwardly adjacent airfoil section, a trailing edge concavity formed in the trailing edge adjacent to the fillet radius relative to a remainder of the trailing edge, the concavity being defined at the root airfoil section and said airfoil section immediately radially outwardly adjacent to the root airfoil section, the concavity being nonrepetitive.

6. The turbofan fan according to claim 5 , wherein the leading edge of each said airfoil has a forward sweep at the tip.

7. The turbofan fan according to claim 5 , wherein a projection of the trailing edge at the root airfoil section intersects the platform at an angle ranging between 65 degrees and 75 degrees relative to an axis of rotation of the turbofan fan.

8. The turbofan fan according to claim 7 , wherein a projection of the trailing edge at the root airfoil section intersects the platform at an angle of approximately 20 degrees.

9. The turbofan fan according to claim 5 , wherein the platform and the airfoils are integrally formed as an integrated bladed rotor.

Assignees

• Stone Paul
• Pratt & Whitney Canada

Inventors

• Stone Paul

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D29/324

  Blades · CPC title

• F01D5/141 Primary

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

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F05D2240/304

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