The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a base, a first side, and a second side, a rail extending from the base of the load beam between the first side and the second side, a tooth running parallel to the longitudinal axis disposed on the first side of the load beam. The rail may comprise at least one of, a convex sidewall having a convex curvature, a concave sidewall having a concave curvature, or a vertical sidewall extending perpendicular to the base. The rail may comprise a sidewall comprising a sidewall step wherein the sidewall has a step cut into a portion of the rail. The rail may comprise a tapered sidewall wherein the tapered sidewall extends at an angle to the base.

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 method of joining a first work piece and a second workpiece. The first and second workpieces may be rotor wheels of a rotor for a turbomachine. At least one of the workpieces includes an oxide dispersion strengthened alloy material and the first and second work pieces may be joined by welding a cladding on at least one of the workpieces to the other of the workpieces, without welding a substrate of the at least one workpiece which includes an oxide dispersion strengthened alloy material.

A turbomachine component having a main body and a multilayer coating, which is applied directly to the main body is provided. The multilayer coating is at least 5 μm and at most 35 μm thick and has a plurality of layers applied directly one on top of the other, wherein the layer applied directly to the main body is an adhesion promoting layer, which comprises chromium nitride, and at least one of the remaining layers comprises a hard material.

A composition of matter is generally provided, in one embodiment, a titanium alloy comprising about 5 wt % to about 8 wt % aluminum; about 2.5 wt % to about 5.5 wt % vanadium; about 0.1 wt % to about 2 wt % of one or more elements selected from the group consisting of iron and molybdenum; about 0.01 wt % to about 0.2 wt % carbon; up to about 0.3 wt % oxygen; silicon and copper; and titanium. A turbine component is also generally provided, in one embodiment, that comprises an article made from a titanium alloy. Additionally, methods are also generally provided for making an alloy component having a beta transus temperature and a titanium silicide solvus temperature.

The invention relates to a method for producing a blade (10) for a turbo machine, especially for an aviation engine, comprising at least the following steps: provision of a monocrystalline or polycrystalline basic body (14) with a supporting surface (16), and generative construction of a blade airfoil (12) of the blade (10) on the supporting surface (16) by layer-by-layer melting and/or sintering of a metallic and/or ceramic powder consisting of a first material (18) or material mixture; and separation of the blade airfoil (12) from the supporting surface (16) of the basic body (14) on a parting surface (20) of the blade airfoil (12).

A further aspect of the invention relates to a blade which is obtainable and/or is obtained by means of such a method.

A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A shrouded impeller for centrifugal compressors, and methods for manufacturing shrouded impellers for centrifugal compressors are provided. In one embodiment, the method includes manufacturing an impeller base, then depositing by cold spraying at least one layer of metallic material on the surface of the frontal part of the impeller corresponding to the shroud of the impeller and machining the impeller to complete and finish the structure thereof. The at least one layer deposited by cold spraying may include grooves adapted to optimize the dynamic behavior of the impeller by modifying and tuning the local natural frequencies.