Abstract: Laminate components and methods for forming the same are provided. In one exemplary aspect, one or more features are laser cut into or along a laminate component or laminate sections thereof. The features are laser cut into or along the laminate component in an atmosphere. In this manner, and oxide layer is formed on the laser cut surfaces of the future. The features are laser cut into or along the laminate component or laminate sections thereof prior to an infiltration process, such as melt infiltration or chemical vapor infiltration. Accordingly, when the laminate component is infiltrated with an infiltration material, the infiltration material is prevented from infiltrating therethrough.

Abstract: In one aspect, the present disclosure is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a shield wall constructed from a first material that includes a first shield wall portion and a second shield wall portion. A spring constructed from a second material includes a first spring portion and a second spring portion. The first shield wall portion is adjacent to the first spring portion, and the second shield wall portion is adjacent to the second spring portion.

Abstract: The present disclosure is directed to a retention assembly for a gas turbine component including a first and a second gas turbine wall respectively defining a first and a second surface. A retainer, positioned between the first and the second surfaces, includes a flange, which contacts the first surface. A plurality of fingers extends outwardly from the flange. A first finger portion extends away from the first turbine wall toward the second wall. A second finger portion connected to the first finger portion extends substantially parallel to the flange. The second finger portion of a first finger of the plurality of fingers is positioned in a first slot defined in the second surface. The second finger portion of a second finger of the plurality of fingers adjacent to the first finger is positioned on the second surface adjacent to the first slot.

Abstract: Composite components that include features that provide improved wear characteristics at the interface between the composite component and a second component are provided. As one example, a composite component can include an integrally formed discontinuous molded tape (DMT) that defines a wear interface between the component and a second component. The wear interface defined by the DMT may provide improved durability of the composite component and may facilitate more uniform wear at the interface, among other benefits. Methods for manufacturing composite components having discontinuous molded tape wear interfaces are also provided.

Abstract: The present disclosure is directed to a retention assembly for a stationary gas turbine component. The retention assembly includes a first stationary gas turbine wall having a first surface. A retention boss extends outwardly from the first surface. The retention assembly includes a second stationary gas turbine wall having a second surface. A retainer is positioned between the first and the second surfaces. The retainer includes a base wall positioned adjacent to the retention boss. A first sidewall extends outwardly from the base wall, and a second sidewall extends outwardly from the base wall. A first arm extends outwardly from the first sidewall, and a second arm extends outwardly from the second sidewall. Each of the first arm and the second arm includes a plurality of convolutions. At least one of the plurality of convolutions is in contact with the second surface.

Abstract: In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud.

Abstract: The present disclosure is directed to a retention assembly for a stationary gas turbine component. A first stationary gas turbine wall defines a first wall cavity and a second stationary gas turbine wall constructed from a ceramic matrix composite defines a second wall cavity. A pin shaft constructed from a first material includes a first shaft end and a second shaft end. A pin head constructed from the ceramic matrix composite includes a first pin head end and a second pin head end. The pin head defines a pin head cavity extending inward from the first pin head end. The first shaft end is positioned in the first wall cavity, and the second shaft end is positioned in the pin head cavity. The second pin head end is positioned in the second wall cavity. The first material is different from the ceramic matrix composite.

Abstract: In one aspect, the present disclosure is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a shield wall constructed from a first material that includes a first shield wall portion and a second shield wall portion. A spring constructed from a second material includes a first spring portion and a second spring portion. The first shield wall portion is adjacent to the first spring portion, and the second shield wall portion is adjacent to the second spring portion.

Abstract: The present disclosure is directed to a retention assembly for a gas turbine component including a first and a second gas turbine wall respectively defining a first and a second surface. A retainer, positioned between the first and the second surfaces, includes a flange, which contacts the first surface. A plurality of fingers extends outwardly from the flange. A first finger portion extends away from the first turbine wall toward the second wall. A second finger portion connected to the first finger portion extends substantially parallel to the flange. The second finger portion of a first finger of the plurality of fingers is positioned in a first slot defined in the second surface. The second finger portion of a second finger of the plurality of fingers adjacent to the first finger is positioned on the second surface adjacent to the first slot.

Abstract: The present disclosure is directed to a retention assembly for a stationary gas turbine component. A first stationary gas turbine wall defines a first wall cavity and a second stationary gas turbine wall constructed from a ceramic matrix composite defines a second wall cavity. A pin shaft constructed from a first material includes a first shaft end and a second shaft end. A pin head constructed from the ceramic matrix composite includes a first pin head end and a second pin head end. The pin head defines a pin head cavity extending inward from the first pin head end. The first shaft end is positioned in the first wall cavity, and the second shaft end is positioned in the pin head cavity. The second pin head end is positioned in the second wall cavity. The first material is different from the ceramic matrix composite.

Abstract: The present disclosure is directed to a retention assembly for a stationary gas turbine component. The retention assembly includes a first stationary gas turbine wall having a first surface. A retention boss extends outwardly from the first surface. The retention assembly includes a second stationary gas turbine wall having a second surface. A retainer is positioned between the first and the second surfaces. The retainer includes a base wall positioned adjacent to the retention boss. A first sidewall extends outwardly from the base wall, and a second sidewall extends outwardly from the base wall. A first arm extends outwardly from the first sidewall, and a second arm extends outwardly from the second sidewall. Each of the first arm and the second arm includes a plurality of convolutions. At least one of the plurality of convolutions is in contact with the second surface.

Abstract: In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud.