Patent ID: 9080448
Filing Date: 2015-07-14
Classification: F01D,F05D,Y02T

Abstract:
1. A vane segment for a gas turbine engine, comprising: an outer shroud; an inner shroud; a composite airfoil having a span slidably disposed between said outer shroud and said inner shroud, the entirety of the span being configured to move in a flowpath direction, the airfoil being configured at its ends to slide against said outer shroud and inner shroud from a first position to a second position, said airfoil having a passage extending between said outer shroud and said inner shroud; and a spoke extending through said passage between said outer shroud and said inner shroud, wherein said airfoil is moveable in the flowpath direction from the first position to the second position, and in the second position the spoke is operative to limit the movement of said airfoil.