Steel soft wall fan case

Patent metadata

Field	Value
Publication number	US-9945254-B2
Application number	US-201514711854-A
Country	US
Kind code	B2
Filing date	May 14, 2015
Priority date	May 14, 2015
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell.

First claim

The invention claimed is:

1. A turbine engine having a fan case surrounding a set of fan blades rotating about a central axis of a turbine engine, the fan case comprising:
a steel support structure shell including first, second and third annular axial walls of sheet metal in an axial series, the second annular axial wall having a diameter greater than a diameter of the respective first and third annular axial walls, a plurality of radially extending rings including a first ring radially interconnecting the first and second annular axial walls and a second ring radially interconnecting the second and third annular axial walls;
a layer of honeycomb material secured to a radially inner side of the support structure shell;
an annular metallic inner axial wall positioned within and secured to the support structure shell, at least part of the honeycomb material being sandwiched radially between the annular metallic inner axial wall and the second annular axial wall and the annular metallic inner axial wall being embedded in the honeycomb material; and
a layer of containment fabric material wrapped around a radial outer surface of the second annular axial wall.

2. The turbine engine as defined in claim 1 wherein a radial outer edge of the respective first and second rings projects radially outwardly from the second annular axial wall.

3. The turbine engine as defined in claim 1 wherein the support structure shell further comprises a fourth annular axial wall of sheet metal having a diameter smaller than the diameter of the third annular axial wall, and wherein the plurality of radially extending rings further comprises a third ring radially interconnecting the third and fourth annular axial walls.

4. The turbine engine as defined in claim 3 wherein the plurality of the radially extending rings further comprises a front ring extending radially outwardly from a forward end of the first annular axial wall and an aft ring extending radially and outwardly from an aft end of the fourth annular axial wall.

5. The turbine engine as defined in claim 3 wherein a radial outer edge of the third ring projects radially outwardly from the third annular axial wall.

6. The turbine engine as defined in claim 3 wherein the first, second, third and fourth annular axial walls have an equal thickness.

7. The turbine engine as defined in claim 3 wherein the plurality of annular axial walls have a thickness in a range between 0.02 and 0.07 inches.

8. The turbine engine as defined in claim 3 wherein the layer of honeycomb material is axially restricted by the first, second and third rings.

9. The turbine engine as defined in claim 1 wherein the layer of honeycomb material comprises filler-structure honeycomb materials and acoustic honeycomb materials.

10. The turbine engine as defined in claim 1 wherein the annular metallic inner axial wall is aluminium.

11. The turbine engine as defined in claim 3 wherein the plurality of rings comprises forged steel rings.

12. The turbine engine as defined in claim 9 wherein the acoustic honeycomb materials are positioned axially afore and after the fan blades, respectively, forming part of a radially innermost surface of the fan case.

13. The turbine engine as defined in claim 12 wherein the fan case further comprises an abradable tip clearance control layer on a radially inner side of the filler-structure honeycomb and positioned axially between the acoustic materials.

14. A method of fabricating an annular fan case for surrounding a set of fan blades rotating about a central axis of a turbine engine, the method comprising steps of:
a) fabricating a steel support structure shell of the fan case using sheet metal to produce a plurality of annular axial walls positioned in an axial series, and using a plurality of radially extending forged steel rings each to radially interconnect axially adjacent two of the annular axial walls having different diameters, the sheet metal being selected from a thickness range of between 0.02 and 0.07 inches;
b) securing a layer of honeycomb material to a radial inner side of the steel support structure shell, the honeycomb material being axially restricted by the respective radially extending forged steel rings;
c) securing an annular metallic inner axial wall to the steel support structure shell, at least part of the honeycomb material being sandwiched between the metallic annular inner axial wall and one of the annular axial walls, wherein steps (a), (b) and (c) are conducted such that all of the annular axial walls of the sheet metal, the forged steel rings, the annular metallic inner axial wall and the honeycomb material are securely connected together to form a structurally integrated thin-walled assembly with enhanced stiffness; and
d) wrapping a layer of fabric containment material around a radial outer surface of said one of the annular axial walls of the steel support structure shell.

15. The method as defined in claim 14 wherein the radially extending forged steel rings are secured to the steel support structure shell such that a radial outer edge of each forged steel ring projects radially outwardly from the steel support structure shell.

16. The method as defined in claim 14 wherein step (a) comprises securing additional forged steel rings to axially opposed forward and aft ends of the steel support structure shell, respectively, such that the additional forged steel rings extend radially outwardly from the respective forward and aft ends of the steel support structure shell.

17. The method as defined in claim 14 wherein the plurality of annular axial walls made of sheet metal have an equal thickness.

18. The method as defined in claim 14 comprising selecting the layer of fabric containment material from high-strength fibrous fabric including Kevlar®.

19. The method as defined in claim 14 wherein steps (b) and (c) are conducted such that the annular metallic inner axial wall is embedded in the layer of honeycomb material.

Assignees

• Pratt & Whitney Canada

Inventors

• Ivakitch Richard
• Wojtyczka Czeslaw
• Eleftheriou Andreas

Classifications

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2300/171

  Steel alloys · CPC title

• F04D29/023

  especially adapted for elastic fluid pumps · CPC title

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title