GAS TURBINE ENGINE CERAMIC COMPONENT ASSEMBLY ATTACHMENT
A gas turbine engine component assembly includes first and second portions, wherein at least one of the first and second portions is a ceramic material. The first portion includes an aperture having a first angled surface. The second portion is disposed within the aperture and includes a second angled surface adjacent to the first angled surface. The first and second angled surfaces lock the first and second portions to one another under a pulling load. A bonding material operatively secures the first and second angled surfaces to one another.
1 . A gas turbine engine component assembly comprising:
first and second portions, wherein at least one of the first and second portions is a ceramic material, the first portion includes an aperture having a first angled surface, the second portion is disposed within the aperture and includes a second angled surface adjacent to the first angled surface, the first and second angled surfaces locking the first and second portions to one another under a pulling load; and
a bonding material operatively securing the first and second angled surfaces to one another.
2 . The gas turbine engine component assembly according to claim 1 , comprising a keeper disposed between the bonding material and the first and second angled surfaces to indirectly secure the first and second portions to one another in a wedged interface.
3 . The gas turbine engine component assembly according to claim 1 , wherein at least one of the first and second portions are bonded to one another using a transient liquid phase bond.
4 . The gas turbine engine component assembly according to claim 1 , wherein at least one of the first and second portions are bonded to one another using a partial transient liquid phase bond.
5 . The gas turbine engine component assembly according to claim 1 , wherein the first portion is constructed from a ceramic matrix composite.
6 . The gas turbine engine component assembly according to claim 1 , wherein the second portion is constructed from a ceramic matrix composite.
7 . The gas turbine engine component assembly according to claim 2 , wherein the keeper is constructed from a ceramic matrix composite.
8 . The gas turbine engine component assembly according to claim 2 , wherein at least one of the first and second portions and the keeper is constructed from a metal alloy.
9 . The gas turbine engine component assembly according to claim 1 , wherein the first portion is an airfoil and the second portion is a shroud.
10 . The gas turbine engine component assembly according to claim 2 , wherein the first and second portions are constructed from a ceramic matrix composite.
11 . The gas turbine engine component assembly according to claim 10 , wherein each of the first and second portions and the keeper are constructed from a ceramic matrix composite.
12 . The gas turbine engine component assembly according to claim 1 , wherein the first portion extends in a longitudinal direction, the first and second angled surfaces are canted in the same direction with respect to the longitudinal direction.
13 . The gas turbine engine component assembly according to claim 12 , wherein the longitudinal direction corresponds to a direction of the pulling load.
14 . The gas turbine engine component assembly according to claim 1 , wherein the bonding material directly secures the first and second angled surfaces to one another.
15 . A gas turbine engine airfoil comprising:
an airfoil and a shroud, wherein at least one of the airfoil and the shroud is a ceramic material, the shroud includes an aperture having a first angled surface, the airfoil is disposed within the aperture and includes a second angled surface adjacent to the first angled surface, the first and second angled surfaces locking the airfoil and the shroud to one another under a pulling load; and
a bonding material operatively securing the first and second angled surfaces to one another.
16 . The gas turbine engine airfoil according to claim 15 , comprising a keeper disposed between the bonding material and the first and second angled surfaces to indirectly secure the airfoil and the shroud to one another in a wedged interface.
17 . The gas turbine engine airfoil according to claim 15 , wherein the bonding material directly secures the first and second angled surfaces to one another.
18 . The gas turbine engine airfoil according to claim 15 , wherein the airfoil extends in a radial direction, the first and second angled surfaces are canted in the same direction with respect to the radial direction, wherein the radial direction corresponds to a direction of the pulling load.
19 . The gas turbine engine airfoil according to claim 15 , wherein at least one of the airfoil and the shroud are bonded to one another using a transient liquid phase bond.
20 . The gas turbine engine airfoil according to claim 15 , wherein at least one of the airfoil and the shroud are bonded to one another using a partial transient liquid phase bond.