The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

A turbine blade includes a platform with an internal cavity formed therein and an airfoil extending radially from the platform. The turbine blade includes a first portion made from ceramic matrix composite materials and a second portion made from superalloy materials. The first and second portions are selectively connected to each other via a spur and include an internal cooling circuit extending across both the first and second portions for circulating coolant therethrough. At least one supply passage extends between the internal cooling circuit and the internal platform cavity and includes an array of pin fins and turbulators for diverting coolant to the internal platform cavity.

Provided is a Ni-based single crystal superalloy containing 6% by mass or more and 12% by mass or less of Cr, 0.4% by mass or more and 3.0% by mass or less of Mo, 6% by mass or more and 10% by mass or less of W, 4.0% by mass or more and 6.5% by mass or less of Al, 0% by mass or more and 1% by mass or less of Nb, 8% by mass or more and 12% by mass or less of Ta, 0% by mass or more and 0.15% by mass or less of Hf, 0.01% by mass or more and 0.2% by mass or less of Si, and 0% by mass or more and 0.04% by mass or less of Zr, and optionally containing at least one element selected from B, C, Y, La, Ce, and V, with a balance being Ni and inevitable impurities.

A turbine part, such as a turbine blade or a distributor fin, for example, including a substrate made of superalloy based on monocrystalline nickel, including rhenium and/or ruthenium, and having a γ′-NisAI phase that is predominant by volume and a γ-Ni phase, the part also including a sublayer made of metal superalloy based on nickel covering the substrate, wherein the sublayer has a γ′-NisAI phase that is predominant by volume and wherein the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part including a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a γ′-NisAI phase, on a substrate made of superalloy based on nickel including rhenium and/or ruthenium.

A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.

Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN) for the hub disk and a maximum critical temperature for the rotor blades (T.sub.BLADE.sub._.sub.MAX) is established such that T.sub.BLADE.sub._.sub.MAX is less than T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than T.sub.DISK.sub._.sub.PROCESS.sub._.sub.MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below T.sub.BLADE.sub._.sub.MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.

A method treats a brush seal at a tip end of the brush seal. The method includes contacting the tip end of the brush seal to an oxidation-resistant, wear-resistant coating composition and heat-treating a distal portion of the bristles to form an oxidation-resistant, wear-resistant coating on the distal portion from the oxidation-resistant, wear-resistant coating composition. A brush seal includes a brush support and bristles extending from the brush support with a distal portion coated by an aluminide diffusion coating. A brush seal assembly includes a non-rotary component and a rotary component. The non-rotary component includes a brush seal including a bristle pack. The bristle pack includes bristles extending from a brush support with a distal portion coated by an aluminide diffusion coating. The rotary component has a sealing surface contacting the distal portion of the brush seal to form a turbine seal between the rotary component and the non-rotary component.

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 invention relates to a nickel-based superalloy comprising, in percentages by mass, 5.0 to 6.0% aluminum, 6.0 to 9.5% tantalum, 0 to 1.50% titanium, 8.0 to 10.0% cobalt, 6.0 to 7.0% chromium, 0.30 to 0.90% molybdenum, 5.5 to 6.5% tungsten, 0 to 2.50% rhenium, 0.05 to 0.15% hafnium, 0.70 to 4.30% platinum, 0 to 0.15% silicon, the remainder being nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and a turbomachine comprising such a blade.

A method of repairing a superalloy component includes a series of sequential steps. The steps are, cleaning the component, applying brazing material to the component, heat treating the component, inspecting the component, preparing the surface of the component, welding the component, and performing a second inspection of the component. The superalloy component is comprised of a high gamma prime superalloy.