Abstract: A rotor for use in an aircraft engine, that has been repaired by (a) welding together a first portion of a damaged blade of the rotor and a second portion of metal to form a weld nugget, (b) compressively stressing the weld nugget throughout its volume, and (c) heat treating the compressively stressed weld nugget to recrystallize metal therein.

Abstract: A method for joining first and second metal portions includes welding together the portions such that a weld nugget joins them, compressively stressing the weld nugget throughout its volume, and heat treating the compressively stressed weld nugget to recrystallize metal therein. A method for strengthening a metal element includes imparting compressive stress within a region of the metal element, and heat treating it such that metal of the region recrystallizes with a finer grain structure than was present in the region before the step of imparting the compressive stress. A repaired metal part includes a first, original section made of metal alloy, and a second, repair section of metal alloy joined to the original section by a recrystallized metal weld having crystals within +/?3 ASTM-112 grain sizes of the size of the crystals of the original and repair sections.

Abstract: A rotor for use in an aircraft engine, that has been repaired by (a) welding together a first portion of a damaged blade of the rotor and a second portion of metal to form a weld nugget, (b) compressively stressing the weld nugget throughout its volume, and (c) heat treating the compressively stressed weld nugget to recrystallize metal therein.

Abstract: A method for joining first and second metal portions includes welding together the portions such that a weld nugget joins them, compressively stressing the weld nugget throughout its volume, and heat treating the compressively stressed weld nugget to recrystallize metal therein. A method for strengthening a metal element includes imparting compressive stress within a region of the metal element, and heat treating it such that metal of the region recrystallizes with a finer grain structure than was present in the region before the step of imparting the compressive stress. A repaired metal part includes a first, original section made of metal alloy, and a second, repair section of metal alloy joined to the original section by a recrystallized metal weld having crystals within +/?3 ASTM-112 grain sizes of the size of the crystals of the original and repair sections.

Abstract: A method for producing a die tool includes forming a substantially complete face plate of the die tool utilizing an additive manufacturing process, forming a support structure of the die tool independently from the face plate, and coupling the face plate with the support structure. A die tool for use in composite manufacturing includes a face plate and stiffening structure integrated with the face plate. The stiffening structure forms one or more hollow channels that transport fluid for heating or cooling during the composite manufacturing. A die tool for use in composite manufacturing includes a face plate and a support structure coupled with the face plate. A ratio of weight of the support structure to weight of the die tool is less than 0.33.