Variable area turbine nozzle with a position selector

A gas turbine engine, comprising:

• a plurality of variable nozzles, each variable nozzle having
• an outer shroud;
• an inner shroud located radially inward from the outer shroud;
• a variable nozzle airfoil extending radially between the outer shroud and the inner shroud, the variable nozzle airfoil including a vane shaft extending radially outward from the variable nozzle airfoil through the outer shroud;
• and
• a position selector coupled with the variable nozzle airfoil to fixedly lock the variable nozzle airfoil into one of a plurality of preselected positions;
• a variable outer-housing located radially outward from the plurality of variable nozzles;
• an inter turbine duct axially preceding the variable nozzles, the inter turbine duct having
• an outer wall, and
• an inner wall located radially inward from the outer wall,
• wherein the outer wall and the inner wall are configured to diverge as the inter turbine duct extends towards the variable nozzles.

A method of operating a gas turbine engine, the method comprising:

• providing a position selector with a discrete number of variable nozzle airfoil clocking positions;
• selecting one of the clocking positions of the position selector;
• rotating a variable nozzle airfoil while the gas turbine engine is not operating by rotating the position selector into the selected clocking position;
• and
• fixing the angle of die variable nozzle airfoil and clocking position of the position selector.