Case with ballistic liner

Patent metadata

Field	Value
Publication number	US-10724397-B2
Application number	US-201715836254-A
Country	US
Kind code	B2
Filing date	Dec 8, 2017
Priority date	Feb 16, 2012
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.

First claim

What is claimed:

1. A case for a gas turbine engine comprising:
a plurality of distinct case sections in axial series, the case sections including, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section, the forward shell section, the containment section, and the aft shell section being formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers, and the flange section being formed of a second plurality of non-crimp fabric layers, wherein the flange section excludes unidirectional roving fiber layers and the plurality of unidirectional roving fiber layers do not have stitching or weaves;
a ballistic liner attached with the containment section;
an abradable layer radially inboard of the ballistic liner; and
a fiberglass layer encapsulating the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.

2. The case for a gas turbine engine as recited in claim 1 , wherein at least one of the plurality of unidirectional roving fiber layers is at a 0 degree direction with respect to an engine axis.

3. The case for a gas turbine engine as recited in claim 1 , wherein at least one of the plurality of unidirectional roving fiber layers is at a 90 degree direction with respect to an engine longitudinal axis.

4. The case for a gas turbine engine as recited in claim 1 , wherein each of the plurality of non-crimp fabric layers includes a first ply at a +θ orientation and a second ply at a −θ orientation relative to the engine longitudinal axis.

5. The case for a gas turbine engine as recited in claim 4 , wherein θ is between 0-80 degrees with respect to an engine longitudinal axis.

6. The case for a gas turbine engine as recited in claim 1 , wherein the containment section is approximately 0.25-1.0 inches thick.

7. The case for a gas turbine engine as recited in claim 1 , wherein the ballistic liner includes a plurality of woven aramid fibers impregnated with resin.

8. A case for a gas turbine engine comprising:
a plurality of distinct case sections in axial series, the case sections including, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section, the forward shell section, the containment section, and the aft shell section being formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers, and the flange section being formed of a second plurality of non-crimp fabric layers, wherein the plurality of unidirectional roving fiber layers do not have stitching or weaves; and
a fiberglass layer encapsulating the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.

9. The case for a gas turbine engine as recited in claim 8 , wherein at least one of the plurality of unidirectional roving fiber layers is at a 0 degree direction with respect to an engine axis, and at least one of the plurality of unidirectional roving fiber layers is at a 90 degree direction with respect to an engine longitudinal axis.

10. The case for a gas turbine engine as recited in claim 8 , wherein each of the plurality of non-crimp fabric layers includes a first ply at a +θ orientation and a second ply at a −θ orientation relative to the engine longitudinal axis.

11. The case for a gas turbine engine as recited in claim 10 , wherein θ is between 0-80 degrees with respect to an engine longitudinal axis.

12. The case for a gas turbine engine as recited in claim 11 , wherein the containment section is approximately 0.25-1.0 inches thick.

13. The case for a gas turbine engine as recited in claim 12 , further comprising a ballistic liner attached with the containment section, and the ballistic liner includes a plurality of woven aramid fibers impregnated with resin.

14. A gas turbine engine comprising:
a fan;
a compressor section;
a combustor;
a turbine section; and
a fan case surrounding the fan, the fan case including,
a plurality of distinct case sections in axial series, the case sections including, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section, the forward shell section, the containment section, and the aft shell section being formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers, and the flange section being formed of a second plurality of non-crimp fabric layers, wherein the plurality of unidirectional roving fiber layers do not have stitching or weaves,
a ballistic liner attached with the containment section, and
a fiberglass layer encapsulating the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Lussier Darin S
• Voleti Sreenivasa R
• Robertson Jr Thomas J
• Quinn Christopher M

Classifications

• B29C70/226

  the structure comprising mainly parallel filaments interconnected by a small number of cross threads · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B29D99/006

  Producing casings, e.g. accumulator cases · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• B29C70/202

  arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC] (B29C70/207 takes precedence) · CPC title