An apparatus and method relating to a film-hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film-hole.

A heat shield (100) and method for assembling such is disclosed. The heat shield (100) may comprise an outer wall (122) and an inner wall (124). The outer wall (122) includes a first member (130), a flange (132) extending outward from the first member (130) and a first inner edge (134). The first member (130) extends from the flange (132) to the first inner edge (134). The inner wall (124) includes a second member (140), a rim (142) extending outward from the second member (140) and a second inner edge (144). The second member (140) extends from the rim (142) to the second inner edge (144). The inner wall (124) is spaced apart from the outer wall (122), the first and second edges form an air gap (146) between them, and the inner wall (124) and the outer wall (122) form a cavity (148).

A heat shield (100) and method for assembling such is disclosed. The heat shield (100) may comprise an outer wall (122) and an inner wall (124). The outer wall (122) includes a first member (130), a flange (132) extending outward from the first member (130) and a first inner edge (134). The first member (130) extends from the flange (132) to the first inner edge (134). The inner wall (124) includes a second member (140), a rim (142) extending outward from the second member (140) and a second inner edge (144). The second member (140) extends from the rim (142) to the second inner edge (144). The inner wall (124) is spaced apart from the outer wall (122), the first and second edges form an air gap (146) between them, and the inner wall (124) and the outer wall (122) form a cavity (148).

In a jet engine having a core that sources a first flow of fluid and a component (such as a fan, a pump, and/or a bleed line) that sources a second flow of fluid, and where the first flow of fluid will typically have, at least during ordinary operation, a higher temperature than the second flow of fluid, at least one flow aperture formed by a first passageway to receive at least a portion of the aforementioned second flow of fluid, wherein that first passageway is comprised of at least one material that (by design and intent) deflects as a function of temperature such that a flow of the second flow of fluid through the at least one flow aperture is thereby desirably modulated.

A turbomachine component, particularly a gas turbine engine component, has at least one part built in parts from a curved or planar panel, particularly a sheet metal, the part having a plurality of cooling channels via which a cooling fluid, particularly air, is guidable, wherein at least one of the plurality of cooling channels has a continuously tapered section. The at least one of the plurality of cooling channels has a single inlet port from a first surface of the panel and a single outlet port for the cooling fluid to another surface, particularly a surface opposite to the first surface, or to the first surface. Further the panel is built via laser sintering or laser melting or direct laser deposition. A gas turbine engine is equipped with such a component. A method of manufacturing includes incorporating cooling channels having a continuously tapered section.

A method is provided in which a resin coating is applied to a surface of a preform. The resin coating includes a carbonaceous resin and a particulate. The preform is added to a tooling. The preform, which is positioned in the tooling, is cured. The tooling is removed. The resin coating on the surface of the preform is pyrolyzed to form a resin carbon-char layer on the surface of the preform. The preform and the resin carbon-char layer are infiltrated with silicon to form a ceramic matrix composite (CMC) component including a layer of silicon carbide. During the infiltration, the silicon reacts with carbon in the resin carbon-char layer to form the layer of silicon carbide on the preform.

A method is provided in which a resin coating is applied to a surface of a preform. The resin coating includes a carbonaceous resin and a particulate. The preform is added to a tooling. The preform, which is positioned in the tooling, is cured. The tooling is removed. The resin coating on the surface of the preform is pyrolyzed to form a resin carbon-char layer on the surface of the preform. The preform and the resin carbon-char layer are infiltrated with silicon to form a ceramic matrix composite (CMC) component including a layer of silicon carbide. During the infiltration, the silicon reacts with carbon in the resin carbon-char layer to form the layer of silicon carbide on the preform.

An exhaust-gas turbocharger (1) having a shaft (2), a turbine wheel (5), which is fastened to the shaft (2), and a heat throttle (8) between the shaft (2) and the turbine wheel. An end face (3) of the shaft (2) is provided with a protrusion (4), with an outside diameter (A.sub.4) which is smaller than the outside diameter (A.sub.2) of the shaft (2). The turbine wheel (5) has a hollow receiving portion (7), which is formed integrally on the wheel rear side (6) and the inside diameter (I.sub.7) corresponds to the outside diameter (A.sub.4) of the protrusion (4) and the outside diameter (A.sub.7) corresponds to the outside diameter (A.sub.2) of the shaft (2). The protrusion (4) engages into the receiving portion (7). The heat throttle (8) is formed by a cavity (8A, 8B), which has an outside diameter (A.sub.8) which is smaller than the outside diameter (A.sub.4) of the protrusion (4) and extends from the protrusion (4) into the receiving portion (7).

An exhaust-gas turbocharger (1) having a shaft (2), a turbine wheel (5), which is fastened to the shaft (2), and a heat throttle (8) between the shaft (2) and the turbine wheel. An end face (3) of the shaft (2) is provided with a protrusion (4), with an outside diameter (A.sub.4) which is smaller than the outside diameter (A.sub.2) of the shaft (2). The turbine wheel (5) has a hollow receiving portion (7), which is formed integrally on the wheel rear side (6) and the inside diameter (I.sub.7) corresponds to the outside diameter (A.sub.4) of the protrusion (4) and the outside diameter (A.sub.7) corresponds to the outside diameter (A.sub.2) of the shaft (2). The protrusion (4) engages into the receiving portion (7). The heat throttle (8) is formed by a cavity (8A, 8B), which has an outside diameter (A.sub.8) which is smaller than the outside diameter (A.sub.4) of the protrusion (4) and extends from the protrusion (4) into the receiving portion (7).

A shield member is disposed over a gap between platform portions of adjacent turbine rotor blades, made from a ceramic matrix composite, and configured to shield the gap between the platform portions.