Back to results
US 2019/0153879 A1Published application
Airfoil for a gas turbine engine having insulating materials
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsDaniel K. Vetters, Ted J. Freeman
Life of this patent
Estimating the term…
Abstract
An airfoil adapted for use in a gas turbine engine is disclosed. The airfoil may include components made from ceramic materials. The airfoil may include insulating material to thermally isolate portions of the airfoil.
Claims20
An airfoil adapted for use in a gas turbine engine, the airfoil comprising
- a ceramic matrix composite skin that provides a pressure side and a suction side of the airfoil that extends from a leading edge to a trailing edge of the airfoil, the ceramic matrix composite skin shaped to define an internal cavity between the pressure side and the suction side of the airfoil sized to carry a cooling air flow,
- a ceramic matrix composite reinforcement rib that extends across the internal cavity between the pressure side and the suction side of the airfoil to reinforce the ceramic matrix composite skin, and
- an insulating layer having a thermal conductivity lower than that of the ceramic matrix composite reinforcement rib that engages at least one side of the ceramic matrix composite reinforcement rib to thermally insulate the ceramic matrix composite reinforcement rib from temperatures in the internal cavity.
An airfoil adapted for use in a gas turbine engine, the airfoil comprising
- a skin that provides a pressure side and a suction side of the airfoil that extends from a leading edge to a trailing edge of the airfoil,
- a reinforcement rib that extends across an internal cavity defined by the skin between the pressure side and the suction side of the airfoil, and
- an insulating layer that is engages at least one side of the reinforcement rib to thermally insulate the reinforcement rib.
A method of making an airfoil for a gas turbine engine, the method comprising
- producing a ceramic matrix composite component including a skin and a reinforcement rib, the skin shaped to provide a pressure side and a suction side of the airfoil that extends from a leading edge to a trailing edge of the airfoil, and the reinforcement rib shaped to extend across an internal cavity of the skin between the pressure side and the suction side of the airfoil, and
- placing an insulating layer in contact with the reinforcement rib that so that the insulating layer engages at least one side of the ceramic matrix composite reinforcement rib to thermally insulate the ceramic matrix composite reinforcement rib from temperatures in the internal cavity of the skin.
Dependencies are inferred from the claim text.