Adhesive pattern for fan case conformable liner

Patent metadata

Field	Value
Publication number	US-9651059-B2
Application number	US-201213728200-A
Country	US
Kind code	B2
Filing date	Dec 27, 2012
Priority date	Dec 27, 2012
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive. The adhesive covers at least a portion of the liner surface area, and can have interruptions used to tune the compliance of the adhesive layer.

First claim

What is claimed is:

1. A fan section of a gas turbine engine comprising:
a fan case,
a septum radially inward of the fan case having a septum surface with a septum surface area,
a continuous ring-shaped conformable liner with a liner surface having a liner surface area; and
an adhesive layer attaching the liner surface to the septum surface, wherein the adhesive layer includes interruptions provided by voids of unapplied adhesive on both the liner surface area and the septum surface area; wherein
the voids of unapplied adhesive define open areas radially between the liner surface area and the septum surface area to provide a reduced bond surface area.

2. The fan section of claim 1 , wherein the liner is a metallic material with a coefficient of thermal expansion greater than 8E-06/deg.F.

3. The fan section of claim 2 , wherein the fan case is constructed from a composite material with a coefficient of thermal expansion less than 4E-06/deg.F.

4. The fan section of claim 3 , comprising a honeycomb structure supported radially inward from and on the fan case, the liner radially inward of the honeycomb structure.

5. The fan section of claim 4 , wherein the liner supports a rub strip comprised of an abradable material and arranged radially inward of the liner.

6. The fan section of claim 5 , additionally including circumferentially arranged fan blades disposed within the fan case, wherein the fan blades each have a tip immediately adjacent to the rub strip.

7. The fan section of claim 1 , wherein the adhesive layer has a thickness in the range of 0.010 inch-0.250 inch (0.254 mm-6.35 mm).

8. The fan section of claim 1 , wherein the fan case has a first coefficient of thermal expansion and the liner has a second coefficient of thermal expansion different from the first coefficient of thermal expansion.

9. The fan section of claim 1 , wherein the adhesive layer has an elongation to failure of greater than 200%.

10. The fan section of claim 9 , wherein the adhesive is an elastomeric silicone.

11. The fan section of claim 9 , wherein the adhesive is a polysulfide rubber.

12. The fan section of claim 1 , wherein the adhesive has at least one perforation providing the voids.

13. The fan section of claim 12 , wherein the at least one perforations have a hexagonal shape.

14. The fan section of claim 12 , wherein the at least one perforations have a rectangular shape.

15. The fan section of claim 12 , wherein the at least one perforations have a triangular shape and are arranged in an isogrid pattern.

Assignees

• United Technologies Corp

Inventors

• Robertson Jr Thomas J
• Lussier Darin S
• Stackhouse Kirk D
• Santana Johan

Classifications

• F05D2250/283

  honeycomb · CPC title

• F04D29/526 Primary

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

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F01D11/127

  with a deformable or crushable structure, e.g. honeycomb · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title