A method for assembling a flow path assembly of a gas turbine engine, the flow path assembly comprising an inner wall and a unitary outer wall including a combustor portion and a turbine portion, the combustor portion of the unitary outer wall extending through a combustion section of the gas turbine engine and the turbine portion of the unitary outer wall extending through at least a first turbine stage and a second turbine stage of a turbine section of the gas turbine engine, wherein the turbine portion of the unitary outer wall comprises an outer band of a nozzle portion of the first turbine stage, a shroud of a blade portion of the first turbine stage, an outer band of a nozzle portion of the second turbine stage, and a shroud of a blade portion of the second turbine stage, and wherein the combustor portion and the turbine portion of the unitary outer wall are integrally formed as a single unitary structure, and the method comprising:
- inserting a plurality of nozzle airfoils through a plurality of openings defined in the unitary outer wall;
- and
- securing the plurality of nozzle airfoils to prevent them from retracting from the plurality of openings.