Containment ring for gas turbine engine
A casing for a gas turbine engine, including: an inner ring portion that provides a gaspath and structural features of the casing; an outer ring portion; and an inner ceramic layer arranged radially between the inner ring portion and the outer ring portion, wherein the inner ceramic layer is bonded directly to an inner surface of the outer ring portion such that the combination of the outer ring portion and the inner ceramic layer provide both containment and primary structural features of the casing.
1. A casing for a gas turbine engine, comprising:
an inner ring portion that provides a gaspath and structural features of the casing;
an outermost ring portion; and
an inner ceramic layer arranged radially between the inner ring portion and the outermost ring portion, wherein the inner ceramic layer is completely enclosed by the inner ring portion and bonded directly to an inner surface of the outermost ring portion such that the combination of the outermost ring portion and the inner ceramic layer provide both containment and primary structural features of the casing.
2. The casing as in claim 1 , wherein the inner ceramic layer is formed from ceramic comprising silicon carbide or boron carbide or a ceramic matrix composite.
3. The casing as in claim 1 , wherein the outermost ring portion is a ductile metal structure.
4. The casing as in claim 1 , wherein a layer of honeycomb is located between the inner ring portion and the inner ceramic layer.
5. The casing as in claim 1 , wherein the inner ceramic layer is a single piece that circumferentially surrounds an inner surface of the outermost ring portion.
6. The casing as in claim 1 , wherein the inner ceramic layer is curved to match a curvature of the inner surface of the outermost ring portion.
7. The casing as in claim 1 , wherein the inner ceramic layer comprises a plurality of ceramic inner segments that circumscribe the inner surface of the outermost ring portion.
8. The casing as in claim 7 , wherein each of the plurality of ceramic inner segments are curved to match a curvature of the inner surface of the outermost ring portion.
9. The casing as in claim 7 , wherein each of the plurality of ceramic inner segments have a fore and aft end and the aft end of each of the plurality of ceramic inner segments abuts a fore end of an adjacent one of the plurality of ceramic inner segments such that a plurality of joints are provided between each of the plurality of ceramic inner segments.
10. The casing as in claim 7 , wherein an expansion joint is located between each of the plurality of ceramic inner segments.
11. The casing as in claim 7 , wherein each of the plurality of ceramic inner segments have a fore and aft end and the aft end of each of the plurality of ceramic inner segments overlaps a fore end of an adjacent one of the plurality of ceramic inner segments such that a plurality of overlapping joints are provided between each of the plurality of ceramic inner segments.
12. The casing as in claim 11 , wherein the fore and aft end of each of the plurality of ceramic inner segments have a flange configured to mate with a corresponding flange of an adjacent one of the plurality of ceramic inner segments.
13. The casing as in claim 1 , wherein the inner ring portion is formed from a ductile metal and the inner ring portion is formed with a recessed area and an abradable surface is located within the recessed area.
14. The casing as in claim 13 , wherein a layer of honeycomb or foam is located between the inner ring portion and the inner ceramic layer and the layer of honeycomb or foam is bonded to both the inner ceramic layer and the inner ring portion.
15. The casing as in claim 1 , wherein the casing is a fan casing.
16. A gas turbine engine, comprising:
a fan having a plurality of fan blades;
a casing surrounding the plurality of fan blades, the casing comprising:
an inner ring portion that provides a gaspath and structural features of the casing;
an outermost ring portion; and
an inner ceramic layer arranged radially between the inner ring portion and the outermost ring portion, wherein the inner ceramic layer is completely enclosed by the inner ring portion and bonded directly to an inner surface of the outermost ring portion such that the combination of the outermost ring portion and the inner ceramic layer provide both containment and primary structural features of the casing.
17. The gas turbine engine as in claim 16 , wherein the inner ring portion is formed with a recessed area and an abradable surface is located within the recessed area and the abradable surface is aligned with plurality of fan blades.
18. The gas turbine engine as in claim 16 , wherein the outermost ring portion is a ductile metal structure or composite material and a layer of honeycomb is located between the inner ring portion and the inner ceramic layer.
19. The gas turbine engine as in claim 16 , wherein the inner ceramic layer is a single piece that circumferentially surrounds an inner surface of the outermost ring portion.
20. The gas turbine engine as in claim 16 , wherein the inner ceramic layer comprises a plurality of ceramic inner segments that circumscribe the inner surface of the outermost ring portion.