Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the vane (14), the vane (14) further comprising an internal cavity between the lateral walls (15), which cavity is intended for passing a vane-cooling fluid, with a fluid inlet opening (19) opening through said first platform (12), characterized in that a gyroid surface network (18) fills at least part of the cavity, being arranged therein so as to guide the cooling fluid, and is in contact with at least part of the lateral walls (15).

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

A blade outer air seal includes a seal body that has a channel on a radially inner side that defines a first height portion outside of the channel and a second height portion within the channel. A first cavity is in the first height portion and a second cavity is in the second height portion. An abradable coating is over the radially inner side and fills the first and second cavities.

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

A blade outer air seal includes a seal body that has a channel on a radially inner side that defines a first height portion outside of the channel and a second height portion within the channel. A first cavity is in the first height portion and a second cavity is in the second height portion. An abradable coating is over the radially inner side and fills the first and second cavities.

A method for producing a vibration-damping structure combination for damping vibrations for movable masses, having a first structure and a further structure, the further structure movable within a stop surface defined by a first structure surface of the first structure. The method includes a) providing the first structure, having the first structure surface and which defines a coating surface of a coating at least in some sections; b) coating the first structure surface of the first structure with the coating, the coating surface of the coating being applied such that a cavity is formed; c) filling the cavity with the filler; d) curing the filler until the further structure having a further structure surface is formed, which lies against the coating surface; and e) removing the coating, the further structure thus being movable relative to the first structure within the stop surface defined by the first structure surface.

A cooling structure for a turbine airfoil includes: a lattice structure body formed such that a first rib set and a second rib set arranged in a cooling passage are stacked on each other in a lattice pattern; and lattice communication portions that allow passages formed between ribs of the first rib set to communicate with passages formed between ribs of the second rib set. Each of the first and second rib sets has rib walls each including a pair of ribs that are inclined in directions opposite to each other relative to an imaginary boundary line extending in a movement direction of a cooling medium and that are in contact with each other on the imaginary boundary line. A plurality of lattice communication portions are formed between two lattice communication portions at opposite end portions of each rib that forms the rib wall.

A cascade assembly for a jet engine thrust reverser comprising an inflow cascade, an outflow cascade, and fasteners. The inflow cascade has a plurality of inflow vanes, a plurality of inflow strongbacks, and a front inflow flange. The outflow cascade has a plurality of outflow vanes, a plurality of outflow strongbacks, and a front outflow flange, wherein each of the plurality of outflow strongbacks are parallel to each other. The fasteners extend through the front inflow flange and the front outflow flange.

Delamination of thermal barrier coatings (TBC's) (276) from superalloy substrates (262) of components (260) for turbine engines (80), such as engine blades (92), vanes (104, 106), or castings in transitions (85), is inhibited during subsequent cooling passage (270) formation. Partially completed cooling passages (264), which have skewed passage paths that end at a terminus (268), which is laterally offset from the passage entrance (266), are formed in the superalloy component (260) prior to application of the TBC layer(s) (276). The skewed, laterally offset path of each partially completed cooling passage (264) establishes an overhanging shield layer (269) of superalloy material that protects the TBC layer (276) during completion of the cooling passage (270).

A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element, and one or more pockets are provided in a radially outer side of the fan track liner. One or more dampers for damping vibration of the fan track liner are positioned in each of the one or more pockets and are arranged so as to contact the annular casing element.