Abstract:
PROBLEM TO BE SOLVED: To provide a repairing method of a turbine engine part. SOLUTION: This repairing method of the turbine engine part such as a vane and a blade having air foil comprises to remove an oxide deposit from respective parts of a part indicating damage by crushing or oxidation of heat insulating coating, to remove a ceramic heat insulating layer from the part, and to blend a surface of the part generating nicks, dents and cracks. When the part has a deteriorated aluminum area, the deteriorated area is removed or replenished. A tip part of the part is also recovered when the part is damaged, and cutting capacity of the part is restored by applying polishing to the tip part. Afterwards, ceramic coating is applied to the part. COPYRIGHT: (C)2003,JPO
Abstract:
A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation.
Abstract:
An alloy part is cast in a mold (280) having a part forming cavity (292, 294, 296). The method comprises pouring a first alloy into the mold. The pouring causes: a surface (550) of the first alloy in the part forming cavity to raise relative to the part forming cavity; a branch flow of the poured first alloy to pass upwardly through a first portion (304) of a passageway; and the branch flow to pass downwardly through a second portion (310), of the passageway; solidifying some of the first alloy in the passageway to block the passageway while at least some of the first alloy in the part forming cavity remains molten. A second alloy is poured into the mold atop the first alloy and solidified.
Abstract:
A process for rejuvenating a turbine disk having a plurality of slots includes the steps of determining a depth of a damaged layer containing M23C6 carbide dissolution; and removing the damaged layer from the slots in accordance with the determined depth.
Abstract:
Corrosion and oxidation resistant, high strength, directionally solidified superalloy alloys and articles are described. The articles have a nominal composition in weight percent of about 12% Cr, 9% Co, 1.9% Mo, 3.8% W, 5% Ta, 3.6% Al, 4.1% Ti, 0.015% B, 0.1 % C, up to about 0.02 Zr, balance essentially nickel, and include no intentional additions of hafnium or zirconium, and also have a small amounts of tantalum carbide. The resultant articles have good hot corrosion resistance and superior oxidation resistance and creep properties. The articles are preferably columnar grain, but may also be single crystal.
Abstract:
Advanced High Strength Single Crystal Superalloy Compositions A superalloy composition and single crystal articles of the composition are described. The broad range is 3-12% Cr, 0-3% Mo, 3-10% W, 0-5% Re, 6-12% Ta, 4-7% Al, 0-15% Co, 0-0.045% C, 0-0.02% B, 0-0.1% Zr, 0-0.8% Hf, 0-2% Nb, 0-1% V, 0-0.7% Ti, 0-10% (Ru+Rh+Pd+Os+Ir+Pt), balance essentially Ni. An equation is presented to select the most useful specific compositions from within this range. An exemplary preferred composition is 5.0% Cr, 10.0% Co, 2.0% Mo, 6.0% W, 3.1% Re, 5.6% Al, 9.0% Ta, 0.1% Hf, balance essentially Ni.
Abstract:
MULTI-STEP HEAT TREATMENT FOR SUPERALLOYS This invention relates to a multi-step heat treatment method for increasing the elevated temperature mechanical properties of nickel base superalloys. The heat treatment method is particularly applicable to those conventional alloys which have a cast structure consisting essentially of a gamma matrix containing a gamma prime second phase precipitate and regions of low melting constituents. The effect of the process of the invention is to maximize the volume fraction of the fine gamma prime precipitate, by a solution treatment and reprecipitation, without causing significant incipient melting.
Abstract:
A method of preparing a superalloy component to receive a ceramic thermal barrier coating without an intermediate bond coat is disclosed. The superalloy substrate is degreased, abrasively cleaned, ultrasonically cleaned, washed in an aqueous bath containing a wetting agent, rinsed at least once, and then heat treated in an atmosphere that is non-reactive with the substrate and alumina at a temperature and time sufficient to form a surface alumina layer which is predominantly alumina.