Low hub-to-tip ratio fan for a turbofan gas turbine engine

Patent metadata

Field	Value
Publication number	US-10408223-B2
Application number	US-201715616302-A
Country	US
Kind code	B2
Filing date	Jun 7, 2017
Priority date	Nov 28, 2012
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (R HUB ), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (R TIP ), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (R HUB /R TIP ) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.

First claim

The invention claimed is:

1. A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of fan blades extending from and being integral with the hub to form an integrally bladed rotor, the fan blades circumferentially spaced apart to form a blade row, each of the fan blades of the blade row at least partially axially overlapping circumferentially adjacent ones of the fan blades of the blade row, each of the fan blades having a leading edge extending between the rotor hub and a blade tip, and wherein a ratio of a hub radius to a tip radius (R HUB /R TIP ) of the fan blades within the blade row is less than 0.29, wherein the hub radius (R HUB ) and the tip radius (R TIP ) are measured at the leading edge of the fan blades.

2. The fan as defined in claim 1 , wherein the ratio of the hub radius to the tip radius (R HUB /R TIP ) is less than 0.25.

3. The fan as defined in claim 1 , wherein the ratio of the hub radius to the tip radius (R HUB /R TIP ) is between 0.25 and 0.29.

4. The fan as defined in claim 1 , wherein the rotor hub of the integrally bladed rotor includes a preform having root stubs disposed on the rotor hub at circumferential positions corresponding to at least alternate ones of said fan blades in the single axial blade row, the root stubs being formed on the rotor hub prior to the fan blades being fastened thereto.

5. The fan as defined in claim 4 , wherein the root stubs have airfoils welded thereto to form the fan blades of the integrally bladed rotor.

6. The fan as defined in claim 5 , wherein the airfoils are linear-friction-welded to the respective root stubs.

7. The fan as defined in claim 4 , wherein the preform has said root stubs disposed on the rotor hub for each of the fan blades in the single blade row.

8. The fan as defined in claim 4 , wherein the fan blades having a rearward sweep in a radially inner portion of the leading edge.

9. A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of fan blades integral with the rotor hub to form an integrally bladed rotor having a single blade row, each of the fan blades having a leading edge extending between the rotor hub and an outer blade tip, the fan having a hub-to-tip ratio defined by a hub radius at the leading edge divided by a tip radius at the leading edge, the hub-to-tip ratio being less than 0.25.

10. The fan as defined in claim 9 , wherein the rotor hub of the integrally bladed rotor includes a preform having root stubs disposed on the rotor hub at circumferential positions corresponding to at least alternate ones of said fan blades in the single axial blade row, the root stubs being formed on the rotor hub prior to the fan blades being fastened thereto.

11. The fan as defined in claim 9 , wherein the root stubs have airfoils welded thereto to form the fan blades of the integrally bladed rotor.

12. The fan as defined in claim 11 , wherein the airfoils are linear-friction-welded to the respective root stubs.

13. The fan as defined in claim 11 , wherein the preform has said root stubs disposed on the rotor hub for each of the fan blades in the single blade row.

14. The fan as defined in claim 9 , wherein the fan blades have a rearward sweep in a radially inner portion of the leading edge.

15. A method of manufacturing an integrally bladed fan for a turbofan gas turbine engine, the integrally bladed fan adapted to rotate about a fan centerline axis, the method comprising: providing a rotor hub having an outer peripheral surface defining a hub radius relative to the fan centerline axis; providing a plurality of fan blade airfoils having a predetermined length; and integrally forming the fan blade airfoils and the rotor hub to produce a blade row of the fan blade airfoils on the rotor hub, wherein each of the fan blade airfoils of the blade row at least partially axially overlaps circumferentially adjacent ones of the fan blade airfoils within the blade row, the fan blade airfoils of the blade row thus formed providing a ratio of the hub radius to a tip radius of the fan blade airfoils, measured from the fan centerline axis to tips of the fan blade airfoils at leading edges thereof, of less than 0.29.

16. The method of claim 15 , further comprising forming a rotor hub preform having a number of root stubs circumferentially spaced apart on a periphery of the rotor hub, the root stubs being axially aligned to define said single blade row, and fastening the fan blade airfoils to the root stubs to form fan blades integrally formed with the rotor hub.

17. The method as defined in claim 15 , further comprising selecting the predetermined length of the fan blade airfoils such that the ratio of the hub radius to the tip radius is between 0.25 and 0.29.

18. The method as defined in claim 15 , further comprising selecting the predetermined length of the fan blade airfoils such that the ratio of the hub radius to the tip radius is less than 0.25.

19. The method as defined in claim 15 , further comprising integrally forming circumferentially alternate ones of said fan blade airfoils with the hub preform directly to the outer peripheral surface of the rotor hub preform without root stubs, leaving alternate root stubs on the hub preform to provide access for machine tools between the circumferentially alternate ones of said fan blade airfoils.

Assignees

• Pratt & Whitney Canada

Inventors

• Heikurinen Kari
• Townsend Peter

Classifications

• F04D29/324

  Blades · CPC title

• F04D29/34

  Blade mountings {(for axial flow compressors F04D29/322)} · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• F04D29/388

  characterised by construction · CPC title

• F01D5/14

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title