Abstract: A gas turbine blade for a gas turbine engine includes an attachment, a blade neck portion, a platform, an airfoil, and a shroud. The gas turbine engine has an operating speed range. The blade neck portion extends radially outward from the attachment. The platform is attached to the blade neck portion opposite the attachment. The airfoil extends radially outward from the platform. The airfoil includes a leading edge, a trailing edge, and an axial chord defined between the leading and trailing edges. The axial chord defines a mid-chord point. The shroud is attached to an end of the airfoil. The shroud includes an upper surface and a modal response tuning component attached to the upper surface of the shroud. The modal response tuning component is offset from the mid-chord point a predetermined distance to move modal response of the gas turbine blade outside of the operating speed range.

Abstract: A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.

Abstract: A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.