Ceramic Matrix Composite Component for a Gas Turbine Engine

A method for forming a ceramic matrix composite component of a gas turbine engine, the method comprising:

• laying up a plurality of plies of a ceramic matrix composite material;
• processing the plurality of plies to form a green state component;
• firing the green state component;
• and
• densifying the fired component to produce a final unitary component,
• wherein the unitary component comprises a combustor liner portion and a combustor discharge nozzle stage portion.

A method for forming a ceramic matrix composite component of a gas turbine engine, the method comprising:

• laying up a plurality of plies of a ceramic matrix composite material, wherein laying up the plurality of plies comprises interspersing a plurality of combustor liner plies with a plurality of combustor discharge nozzle stage plies;
• processing the plurality of plies to form a green state component;
• firing the green state component;
• and
• densifying the fired component to produce a final unitary component,
• wherein the unitary component comprises an inner wall and an outer wall, the inner and outer wall defining a combustion chamber adjacent a forward end of the unitary component, and
• wherein the unitary component comprises a nozzle extending from the inner wall to outer wall adjacent an aft end of the unitary component.