Manufactured article and method

A method for fabricating a component, comprising the steps of:

• forming an additively manufactured component having sequentially joined layers of a metallic powder by an additive manufacturing process, wherein the metallic powder includes a nickel-based superalloy or a cobalt-based superalloy or an iron-based alloy, and the additive manufacturing process is selected from the group consisting of direct metal laser melting, direct metal laser sintering, selective laser melting, and electron beam melting;
• applying a braze material to an expected crack location on a surface of the additively manufactured component,
• the braze material includes a nickel-based superalloy material or a cobalt-based superalloy material;
• heating the additively manufactured component to one or more desired heating temperatures for one or more heating dwell time periods, wherein the heating includes:
• heating the additively manufactured component to a first temperature and maintaining the additively manufactured component at the first temperature for a first dwell time period;
• and
• heating the additively manufactured component to a second temperature and maintaining the additively manufactured component at the second temperature for a second dwell time period,
• wherein the first temperature is lower than the second temperature, and wherein the second temperature is at a temperature level where the braze material remains in a solid state;
• cooling the additively manufactured component to a cooling temperature for a cooling dwell time period;
• and
• wherein the braze material fills in a crack formed during the heating, and the additively manufactured component is a gas turbine component or a steam turbine component, and wherein the metallic powder includes a precipitation hardened nickel-based superalloy, which forms a γ′ phase.