Containment ring for gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorNathan Tomes
Life of this patent
Estimating the term…
Abstract
A casing for a gas turbine engine, including: a plurality of layers of a structural material, wherein each layer of the plurality of layers of the structural material are separated from each other by at least one layer of an impact absorbing material, the at least one layer of impact absorbing material being different from the structural material and the impact absorbing material having a radial thickness that is greater than a radial thickness of the structural material, wherein the plurality of layers of the structural material comprises at least three layers.
Claims17
A casing for a gas turbine engine, comprising:
- a multi-layer configuration for absorbing impact forces comprising a plurality of layers of a structural material, wherein each layer of the plurality of layers of the structural material are separated from each other by at least one layer of an impact absorbing material, the at least one layer of impact absorbing material being different from the structural material and the impact absorbing material having a radial thickness that is greater than a radial thickness of the structural material, the plurality of layers of the structural material comprise an inner most layer, at least one intermediate layer and an outer most layer, the inner most layer defining a portion of an interior surface of the casing and the outer most layer defining a portion of an exterior surface of the casing, and the outer most layer includes at least one hairpin feature configured to deform before failure, the at least one hairpin feature having a first radially extending wall portion connected to a second radially extending wall portion, the first radially extending wall portion being spaced from the second radially extending wall portion such that a cavity is defined by the first radially extending wall portion and the second radially extending wall portion, and the at least one intermediate layer being located between the inner most layer and the outer most layer.
A gas turbine engine, comprising:
- a fan having a plurality of fan blades;
- a casing surrounding the plurality of fan blades, the casing comprising:
- a multi-layer configuration for absorbing impact forces comprising a plurality of layers of a structural material, wherein each layer of the plurality of layers of the structural material are separated from each other by at least one layer of an impact absorbing material, the at least one layer of impact absorbing material being different from the structural material and the impact absorbing material having a radial thickness that is greater than a radial thickness of the structural material, the plurality of layers of the structural material comprise an inner most layer, at least one intermediate layer and an outer most layer, the inner most layer defining a portion of an interior surface of the casing and the outer most layer defining a portion of an exterior surface of the casing, and the outer most layer includes at least one hairpin feature configured to deform before failure, the at least one hairpin feature having a first radially extending wall portion connected to a second radially extending wall portion, the first radially extending wall portion being spaced from the second radially extending wall portion such that a cavity is defined by the first radially extending wall portion and the second radially extending wall portion, and the at least one intermediate layer being located between the inner most layer and the outer most layer.
Dependencies are inferred from the claim text.