A sealing system including a first component at least partially manufactured from ceramic fiber composite materials, a second component at least partially manufactured from ceramic fiber composite materials, and a sealing element accommodated between the first component and the second component. The sealing element is designed as a sealing strip. It is provided that at least one recess accommodating the sealing element is formed on the first component and/or on the second component, the recess having a cross-sectional profile including an inner section which is concave toward the sealing element, the radius of curvature of the inner section being selected in such a way that it may be formed with the aid of continuous, curved fibers of the ceramic fiber composite material, the fibers being oriented in such a way that they lie essentially in parallel to the cross-sectional plane of the cross-sectional profile.

Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric.

An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighboring the attachment strap.

A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defining a pressure side and a suction side separated in a circumferential direction. A platform includes a first and second platform portions attached to the root section. Each of the first and second platform portions includes a shoe section and a platform section extending in the circumferential direction from the shoe section to establish a gas path surface, and the shoe sections of the first and second platforms are circumferentially arranged on opposed sides of the root section to capture the root section in a root cavity established between the shoe sections. A method of assembly is also disclosed.

In a pump housing having an interior for accommodating a pump rotor, which may be transferred from a radially compressed state into a radially expanded state, and comprises a housing skin revolving in circumferential direction, as well as at least one reinforcement element, a stretch-resistant element revolving in circumferential direction is provided, which is stretched less than 5% in the expanded state as opposed to the force-free state in circumferential direction, and which limits any further expansion of the pump housing in radial direction.

A water pump has a pump housing 2 having therein a pump chamber 3; a drive shaft 7 rotatably supported in the pump housing 2; a pulley 5 having a flange wall 5a fixed to one end portion of the drive shaft 7, the pulley 5 being formed integrally with the drive shaft 7 with synthetic resin material containing glass fiber material 25; and an impeller 8 secured to the other end portion of the drive shaft 7 so as to be able to rotate integrally with the drive shaft 7, the impeller 8 being accommodated in the pump chamber 3. Six penetration holes 23 are formed at the flange wall 5a, and the glass fiber material 25 existing around the penetration hole 23 is oriented at random. With this, decrease in strength of the pulley can be suppressed.

An airfoil comprises a wall that defines a leading edge and a trailing edge and one or more cavities located within the wall along with a rib that separates the cavities. The rib or the wall comprises a first split ply that comprises a consolidated section and two or more split sections; wherein the split sections emanate from the consolidated section; and where the split sections define the wall and the cavities of the airfoil.

A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.

A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep.