Method for coating a component for the hot gas duct of a turbomachine

A method for coating a component with a coating material, which component is provided for arrangement in the hot gas duct in a turbine center frame of a turbomachine, as a hot gas duct panel or as a fairing of a support strut supporting the bearing of the turbine shaft, comprising the steps of:

• keeping the coating material or a precursor thereof in the form of particles in mixture with a binding agent;
• applying a coat of the particle-treated binding agent onto a region of the component the entirety of which is not precoated;
• and
• thermally treating the component with the particle-treated binding agent on it so that the binding agent is released and the coating material remains on the component;
• and
• wherein the second region is a functional surface-area region of the surface of the component that represents a mounting boundary in regard to an assembly of the component with other components in the turbomachine, which remains uncoated, and
• wherein a surface-area proportion of at least 10% of a portion of the surface of the component exposed to the hot gas is coated and at least 20% of the surface exposed to the hot gas is uncoated;
• and
• wherein the particle-treated binding agent is applied prior to the step of thermally treating sequentially in at least two non-coextensive coats, which have at least one partial overlap with one another on the surface of the component providing a progressive stepped coating.