Abstract: A gas turbine engine includes a turbine shroud assembly with a carrier and a plurality of turbine shroud segments. Each turbine shroud segment includes a blade track segment and a mount assembly. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a shroud wall and a mount post that extends radially away from the shroud wall. The mount assembly is configured to couple the blade track segment with the carrier.

Abstract: A gas turbine engine includes a turbine shroud assembly with a carrier and a plurality of turbine shroud segments. Each turbine shroud segment includes a blade track segment and a mount assembly. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a shroud wall and a mount post that extends radially away from the shroud wall. The mount assembly is configured to couple the blade track segment with the carrier.

Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and a CMC foam layer bonded to the first CMC sheet. The CMC foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the CMC foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

Abstract: One aspect provides a fastening strip, including: a central portion comprised of a flexible material and having a first side and a second side, the first side including a first complementary material and the second side including a second complementary material, complementary to the complementary material of the first side; and a grip area disposed on at least the first side of the central portion; wherein the grip area extends substantially an entire length of fastening strip and includes a grip material. Other aspects are described.

Abstract: A thermal barrier coating composition for a ceramic matrix composite is provided. The thermal barrier coating comprises a porous layer and a doped rare earth disilicate layer. The porous layer is located over the doped rare earth disilicate layer. The porous layer includes a fugitive material.

Abstract: One aspect provides a fastening strip, including: a central portion comprised of a flexible material and having a first side and a second side, the first side including a first complementary material and the second side including a second complementary material, complementary to the complementary material of the first side; and a grip area disposed on at least the first side of the central portion; wherein the grip area extends substantially an entire length of fastening strip and includes a grip material. Other aspects are described.

Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

Abstract: A mold system for producing components of a turbine engine. The mold system may enable a configuration of a turbine engine component to be changed in less time than conventional systems. The mold system may include a mold formed from mold plates wherein at least one of the mold plates has at least one mold cavity configured to receive a ceramic insert and a ceramic insert positioned in the at least one mold cavity and including a core making cavity. The ceramic insert may be formed from a material having high compressive strength, good wear resistance, good corrosion resistance, good thermal conductivity, and high toughness, such as but not limited to, graphite partially or fully converted to silicon carbide, silicon carbide, graphite coated with silicon carbide, and other appropriate materials. The ceramic insert may also be formed with other near net shape processes, such as, reaction bonded metal oxides.

Abstract: A method for making a material system includes the steps of: providing a chamber, placing hollow geometric shapes in the chamber, closing the chamber, evacuating air from the chamber, feeding a binder for the shapes into the evacuated chamber to impregnate the geometric shapes, drying the binder permeated geometric shapes, and heating the hollow shapes and binder to provide a unitary, sintered material system.

Abstract: A composite material (10) formed of a ceramic matrix composite (CMC) material (12) protected by a ceramic insulating material (14). The constituent parts of the insulating material are selected to avoid degradation of the CMC material when the two layers are co-processed. The CMC material is processed to a predetermined state of shrinkage before wet insulating material is applied against the CMC material. The two materials are then co-fired together, with the relative amount of shrinkage between the two materials during the firing step being affected by the amount of pre-shrinkage of the CMC material during the bisque firing step. The shrinkage of the two materials during the co-firing step may be matched to minimize shrinkage stresses, or a predetermined amount of prestress between the materials may be achieved. An aluminum hydroxyl chloride binder material (24) may be used in the insulating material in order to avoid degradation of the fabric (28) of the CMC material during the co-firing step.

Abstract: A method of coating an edge surface (30) of an anisotropic ceramic matrix composite material (10) for use in a high temperature environment is disclosed where the edge surface (30) has exposed reinforced fiber layers (20). A laser beam may be used to melt a portion of the ceramic matrix composite material (10) on the edge surface (30) forming a melt layer. The melt layer is retained proximate the edge surface and the laser beam is controlled to form an isotropic protective coating (32, 34) on a portion of the edge surface (30). A method may be used to form a component for use in a high temperature environment that includes directing a laser beam toward a ceramic matrix composite material (10), controlling the laser beam to melt a portion of the ceramic matrix composite material (10) and forming a homogeneous protective coating (32, 34) from a melt layer that exerts compression on at least a portion of the ceramic matrix composite material (10) when the melt layer is cooled.

Abstract: A thermal barrier layer (20) is formed by exposing an oxide ceramic material to a thermal regiment to create a surface heat affected zone effective to protect an underlying structural layer (18) of the material. The heat affected surface layer exhibits a lower strength and higher thermal conductivity than the underlying load-carrying material; however, it retains a sufficiently low thermal conductivity to function as an effective thermal barrier coating. Importantly, because the degraded material retains the same composition and thermal expansion characteristics as the underlying material, the thermal barrier layer remains integrally connected in graded fashion with the underlying material without an interface boundary there between.

Abstract: A joining method for assembling components with complex shapes from CMC elements of simpler shapes. A first CMC element (30) is fabricated and fired to a selected first cured state. A second CMC element (36) is fabricated and left in a green state, or is fired to a second partially cured state that is less complete than that of the first cured state. The two CMC elements (30, 36) are joined in a mating interface that captures an inner joining portion (38) of the second element (36) within a surrounding outer joining portion (32) of the first element (30). The assembled elements (30, 36) are then fired together, resulting in differential shrinkage that compresses the outer joining portion (32) onto the inner joining portion (38), providing a tightly pre-stressed joint. Optionally, a refractory adhesive (42) may be used in the joint. Shrinkage of the outer joining portion (32) avoids shrinkage cracks in the adhesive (42).

Abstract: An oil well swab cup with improved wear characteristics utilizes a single integral reinforcing structure featuring a wear surface forming a substantial portion of the external surface of the cup.