Abstract: Methods are provided for repairing cracks in a damaged section of a gas turbine engine component with an in-situ brazing process. In an embodiment, by way of example only, the method includes applying a braze paste to the damaged section of the component, the braze paste comprising a braze material and an organic binder. The method also includes subjecting the damaged section of the component to a first temperature that is below a brazing temperature of the braze material to thereby substantially decompose and evaporate the organic binder, and heating the braze material using laser energy to a second temperature that is substantially equal to or above the brazing temperature to form the brazed joint on the component.