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 swash plate includes 34.5 to 43.0 wt % of copper (Cu) and 0.5 to 2.8 wt % of silicon (Si), with a remainder of aluminum (Al) and other inevitable impurities.

The invention relates to a method for producing a cast component which has cavity structures, using a 3D pattern of digital geometrical coordinates of the cast component by means of a ceramic mold, said method comprising the use of CNC technology.

A method for manufacturing a bolster of a railway car truck includes providing a drag portion and a cope portion of a mold. In a main body section of the mold, a parting line that separates the drag portion from the cope portion is substantially centered between portions of the mold that define brake window openings in sides of the bolster. One or more cores are inserted into the mold and a molten material is poured into the mold to thereby case the bolster.

A method of casting an assembly is provided that includes forming a structural insert, over-molding the structural insert with a temporary core, and positioning the over-molded structural insert within a cavity of a casting die. The over-molded structural insert is cast within a part, to form the assembly, and the temporary core is removed. The method may also include a temporary core configured to define an alloy flash trim location or locating features to position the structural insert within the cavity of the casting die. Further, the temporary core may define shared features with the structural insert. The part and structural insert may be dissimilar materials such as a part of an aluminum alloy material and a structural insert of a steel alloy material.

A casting core assembly includes a metallic core, a ceramic core having a compartment in which the portion of the metallic core is received, and a ceramic coating at least partially covering the metallic core and the ceramic core.

A ceramic matrix composite (CMC) component, such as a turbine blade for a combustion turbine engine that has a fiber-reinforced, solidified ceramic substrate. The substrate has an inner layer of fibers, for enhancing structural strength of the component. An outer layer of fibers defines voids therein. A thermal barrier coat (TBC) is applied over and coupled to the outer layer fibers, filling the voids. The voids provide increased surface area and mechanically interlock the TBC, improving adhesion between the fiber-reinforced ceramic substrate and the TBC.

Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

Method for casting a turbine component body including; providing a mould defining the external geometry of the component body and providing a core defining an internal geometry of the component body. The core includes a main body defining an internal chamber of the component body and an array of pedestals extending between opposing walls of the internal chamber. A molten material is cast between the mould and the core and the core is then removed after the molten material has solidified. The core is provided using a core die which has an inlet for receiving fluid core material. The core die is configured such as to provide a gradient of injection pressure which decreases from a first position proximal to the inlet to a second position distal to the inlet. The pedestal array is arranged such that the separation of the pedestals increases between the first and second positions.

In a method for removing a carbon-containing pattern material from a casting shell, a first step evaporates and pyrolizes the pattern material to leave carbon and a second step oxidizes the carbon.