Component assembly for variable airfoil systems

A gas turbine engine defining a core air flowpath and a combustion chamber, the gas turbine engine comprising:

• an outer shell at least partially defining a first portion of the core air flowpath and a first portion of the combustion chamber, the outer shell comprising a first array of integral outer shell airfoils that extend inward from an outer shell periphery;
• an inner shell at least partially defining a second portion of the core air flowpath and a second portion of the combustion chamber, the inner shell comprising a second array of integral inner shell airfoils that extend outward from an inner shell periphery;
• and
• an actuator in communication with one of the outer shell and the inner shell,
• wherein the outer shell and the inner shell are one or both of translatable and rotatable relative to one another between a first position and a second position by the actuator.

A component assembly for a gas turbine engine defining a core air flowpath, the component assembly comprising:

• an outer shell comprising a first array of integral outer shell airfoils that extend inward from an outer shell periphery;
• and
• an inner shell comprising a second array of integral inner shell airfoils that extend outward from an inner shell periphery, the first array of integral outer shell airfoils and second array of inner shell airfoils together forming a stage one nozzle for the gas turbine engine;
• wherein the outer shell and the inner shell are one or both of translatable and rotatable relative to one another between a first position during a first operating condition of the gas turbine engine and a second position during a second operating condition of the gas turbine engine.