Turbine blade with heat shield
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsTara G. Schetzel, Ted J. Freeman, David J. Thomas
Life of this patent
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Abstract
An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar, a heat shield arranged around the spar, and a plurality of describe rigid load supports extending between the spar and the heat shield to transfer loads between the heat shield and the spar.
Claims20
An airfoil adapted for use in a gas turbine engine, the airfoil comprising
- a spar comprising metallic materials and formed to include a core body and a tail, the tail shaped to form a trailing edge of the airfoil,
- a heat shield comprising ceramic materials and shaped to extend around the core body to form a leading edge, a forward portion of a pressure side of the airfoil, and a forward portion of a suction side of the airfoil, the heat shield located in spaced-apart relation to the core body to define cooling passages between the spar and the heat shield, and
- a plurality of rigid load supports that extend between the spar and the heat shield to transfer loads from the heat shield to the spar during use in the gas turbine engine while maintaining the cooling passages between the spar and the heat shield.
An airfoil adapted for use in a gas turbine engine, the airfoil comprising
- a spar comprising metallic materials and formed to include a core body and a tail, the tail shaped to form an aft portion of a pressure side of the airfoil, an aft portion of a suction side of the airfoil, and a trailing edge of the airfoil, and
- a heat shield comprising ceramic materials and shaped to extend around the core body to form a leading edge of the airfoil, a forward portion of the pressure side of the airfoil, and a forward portion of the suction side of the airfoil,
- wherein the forward portion of the pressure side is greater than half of the pressure side and the forward portion of the suction side is greater than half of the suction side.
A turbine-blade assembly adapted for use in a gas turbine engine, the turbine-blade assembly comprising
- a root including a root platform and a stem adapted to attach the turbine-blade assembly to the gas turbine engine for rotation about a central axis of the gas turbine engine,
- an airfoil including a spar comprising metallic materials and a heat shield comprising ceramic materials, the spar extending outward from the root platform and formed to include a core body, a tail forming a trailing edge of the airfoil, and an airfoil retainer extending outwardly away from the core body, the heat shield shaped to extend around the core body to form a leading edge, a forward portion of a pressure side of the airfoil, and a forward portion of a suction side of the airfoil, the heat shield located in spaced-apart relation to the core body to define cooling passages between the spar and the heat shield, and
- a tip shroud spaced-apart from the root, the tip shroud formed to include an airfoil retainer aperture extending through the tip shroud, and configured to receive the airfoil retainer of the spar therethrough to couple the spar to the tip shroud.
Dependencies are inferred from the claim text.