Liners for turbomachinery cases

Patent metadata

Field	Value
Publication number	US-2016169044-A1
Application number	US-201514969608-A
Country	US
Kind code	A1
Filing date	Dec 15, 2015
Priority date	Dec 15, 2014
Publication date	Jun 16, 2016
Grant date	—

Abstract

A method of making a liner for a turbomachinery case includes overlaying a reinforcing layer and a release layer. The method also includes spiral coiling the reinforcing layer and the release layer about the axis of the liner such that a radially inner surface of the release layer radially overlays a radially outer surface of the reinforcing layer.

First claim

What is claimed is:

1 . A method of installing a liner in a turbomachinery case, comprising:
overlaying a reinforcing layer and a release layer; spiral coiling the reinforcing layer and the release layer about an axis of the liner, wherein an inner surface of the reinforcing layer radially overlays an outer surface of the reinforcing layer; winding the spiral coiled reinforcing layer about the liner axis in a diameter-reducing direction to form a wound liner having a diameter that is smaller than an inner diameter of the case; and positioning the wound liner axially within the case, whereby the liner unwinds to line the case.

2 . A method as recited in claim 1 , wherein spiral coiling the reinforcing layer and the release layer about the axis further includes overlaying the release layer over the reinforcing layer.

3 . A method as recited in claim 1 , further including vacuum bagging and curing the reinforcing layer.

4 . A method as recited in claim 3 , wherein winding the spiral coiled reinforcing layer about the liner axis in the diameter-reducing direction includes reducing a diameter of spiral-coiled reinforcing layer.

5 . A method as recited in claim 3 , further including unwinding the spiral coiled reinforcing layer about the about the axis in a diameter-expanding direction.

6 . A method as recited in claim 1 , wherein the reinforcing layer is a first reinforcing layer, and further including overlaying a second reinforcing layer over the first reinforcing layer.

7 . A method as recited in claim 6 , wherein spiral coiling includes spiral coiling the release layer, the first reinforcing layer, and the second reinforcing layer about the axis.

8 . A method as recited in claim 7 , wherein spiral coiling includes spiral coiling the first reinforcing layer while contact with the second reinforcing layer about the axis.

9 . A method as recited in claim 1 , wherein the spiral coiling includes wrapping the release layer and the reinforcing layer about a circumference of mandrel, wherein contiguous lengths of release layer and reinforcing layer are both greater than the circumference of the mandrel.

10 . A method as recited in claim 1 , further including axially separating the reinforcing layer into a first liner detail and a second liner detail.

11 . A method of making a fan case, comprising:
reducing a diameter of a liner,
wherein the liner has a reinforcing layer overlaying a release layer,
wherein in the reinforcing layer and the release layer are spiral coiled about an axis of the liner such that an inner surface of the reinforcing layer radially overlays an outer surface of the reinforcing layer;
inserting the liner into an interior of a fan case; and fixing the liner to an interior surface of the fan case.

12 . A method as recited in claim 11 , wherein reducing the diameter of the liner includes winding the liner in a diameter-reducing direction about the liner detail axis.

13 . A method as recited in claim 12 , wherein winding the liner includes sliding the reinforcing layer inner surface circumferentially across the reinforcing layer outer surface.

14 . A method as recited in claim 13 , wherein the release layer radially separates the reinforcing layer inner surface from the reinforcing layer outer surface.

15 . A method as recited in claim 11 , further including expanding the liner diameter by unwinding the liner in a diameter-expanding direction about the liner detail axis.

16 . A case for a gas turbine engine, comprising:
a case body having an interior surface and defining an axis, wherein the interior surface extends circumferentially about the axis; and a liner with a reinforcing layer fixed to the interior surface of the case, wherein the reinforcing layer has a spiral-coiled shape that extends continuously about the interior surface of the case body, wherein the liner has a length that is greater than a diameter of case body.

17 . A case as recited in claim 16 , wherein the liner includes residual tension exerting a force oriented radially outward with respect to an axis of the case body.

18 . A case as recited in claim 16 , wherein the case is a fan case for a gas turbine engine.

19 . A case as recited in claim 16 , wherein the reinforcing layer spirals contiguously about the interior surface of the case body more than once.

20 . A case as recited in claim 16 , wherein a thickness of the liner is more than 20 times a thickness of the reinforcing layer.

Assignees

• United Technologies Corp

Inventors

• Clarkson Steven
• Robertson Jr Thomas J

Classifications

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F01D21/045

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

• F05D2250/25

  helical · CPC title