Case with ballistic liner
View Patent ↗A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.
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 plurality of unidirectional roving fiber layers do not have stitching or weaves;
a ballistic liner bonded to said 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.
2. The case for a gas turbine engine as recited in claim 1 , wherein at least one of said 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 said 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 said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said containment section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said containment section.
5. The case for a gas turbine engine as recited in claim 4 , wherein said containment section is approximately 0.25-1.0 inches thick.
6. The case for a gas turbine engine as recited in claim 4 , wherein said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said forward shell section and said aft shell section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said forward shell section and said aft shell section.
7. The case for a gas turbine engine as recited in claim 6 , wherein said forward shell section and said aft shell section is approximately 0.25 inches thick.
8. The case for a gas turbine engine as recited in claim 1 , wherein said ballistic liner includes a plurality of woven aramid fibers impregnated with resin.
9. The case for a gas turbine engine as recited in claim 1 , wherein each of said 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.
10. The case for a gas turbine engine as recited in claim 9 , wherein +θ is between 0-80 degrees with respect to an engine longitudinal axis.
11. The case for a gas turbine engine as recited in claim 1 , wherein the flange section excludes unidirectional roving fiber layers.
12. The case for a gas turbine engine as recited in claim 1 , further comprising an abradable layer radially inboard of said ballistic liner.
13. The case for a gas turbine engine as recited in claim 12 , further comprising aerodynamic liners located axially forward and axially aft of said abradable liner.
14. The case for a gas turbine engine as recited in claim 13 , wherein said aerodynamic liners are formed of a honeycomb.