The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

Refractory metal cores for manufacturing components of gas turbine engines, manufactured components, and related methods are provided. A refractory metal core includes a trunk configured to attach to a cavity core structure, a first branch extending from the trunk and configured to form a first portion of a cooling circuit in the component, and a second branch extending from the trunk and configured to form a second portion of the cooling circuit in the component. The first branch and the second branch are configured to define fluid exits at two different locations on an exterior of the component.

When a compressor vane or blade for an engine is used in an environment containing abundant foreign substances, deposits originated from the foreign substances are likely to deposit on surfaces of the vane or blade. The compressor vane or blade according to the present disclosure has a base body of the compressor vane or blade; and a coating covering the base body, which consists essentially of one or more selected from the group of molybdenum disulfide and tungsten disulfide.

A turbine apparatus is disclosed including a first article and a second article disposed between the first article and a hot gas path of a turbine. The first article includes at least one first article cooling channel in fluid communication with and downstream from a cooling fluid source, and the second article includes at least one second article cooling channel in fluid communication with and downstream from the at least one first article cooling channel. A method for redundant cooling of the turbine apparatus is disclosed including flowing a cooling fluid from the cooling fluid source through at least one first article cooling channel, exhausting the cooling fluid from the at least one first article cooling channel into at least one second article cooling channel, and flowing the cooling fluid through the at least one second article cooling channel.

A method of forming a thermal barrier coating is disclosed. The method may include providing a solution containing strontium and niobium and applying the solution to a substrate via a chemical solution deposition process to form a first film layer on the substrate. The method may further include pyrolyzing the first film layer and annealing the first film in an air atmosphere to form a strontium niobate coating.

A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0% cobalt, 0.3 to 1.0% molybdenum, 3.0 to 5.0% chromium, 2.5 to 4.0% tungsten, 4.5 to 6.5% aluminum, 0.50 to 1.50% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.

The present disclosure discloses a rare earth tantalate ceramic resisting corrosion of a low melting point oxide. A general chemical formula of the ceramic is RETaO.sub.4. A method for preparing the ceramic includes: weighing RE.sub.2O.sub.3 powder and Ta.sub.2O.sub.5 powder and adding to a solvent to mix, and ball milling the mixed solution with a ball mill to obtain powder A; drying the powder A, and sieving the powder A for a first time to obtain powder B; placing the powder B in a mold for compaction, pre-sintering the powder B to form a block C, cooling the block C to room temperature, grounding the block C with a grinder, and sieving the block C for a second time to obtain powder D; and sintering the powder D to obtain the rare earth tantalate ceramic. The ceramic has high density and strong corrosion resistance to low melting point oxides.

The invention relates to a nickel-based superalloy comprising, in percentages by mass, 4.0 to 5.5% rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0% cobalt, 0.3 to 1.0% molybdenum, 3.0 to 5.0% chromium, 2.5 to 4.0% tungsten, 4.5 to 6.5% aluminum, 0.50 to 1.50% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. The invention also relates to a single-crystal blade (20A, 20B) comprising such an alloy and a turbomachine (10) comprising such a blade (20A, 20B).

Combining a precipitation-hardening nickel-base alloy with a steel or titanium substrate makes it very easy to repair parts, the nickel-base alloy having good erosion-resistant properties. A method for producing is disclosed. In particular for repairing, a component having a substrate, in particular turbine blades made of steel or titanium, in particular made of martensitic or precipitation-hardening chromium-rich steels, with a localized deposition weld or with an affixed shaped part, in which a precipitation-hardening nickel-based alloy is used as the localized deposition weld or as the shaped part, in which a laser powder deposition weld or an arc deposition weld is performed.