Turbine blade assembly with mounted platform
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsTed J. Freeman, Michael A. Kowalkowski
Life of this patent
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Abstract
A turbine blade assembly adapted for use in a gas turbine engine is disclosed in this paper. A primary member of the turbine blade assembly shaped to form an airfoil and comprises ceramic matrix composite materials. A independent platform of the turbine blade assembly is coupled to the primary member of the turbine blade assembly such that the primary member need not be shaped to provide the platform.
Claims20
A turbine blade assembly configured to be rotated about an axis to withdraw mechanical energy from gasses interacting with the turbine blade assembly, the turbine blade assembly comprising
- a primary member comprising ceramic matrix composite materials, the primary member shaped to form an airfoil and an attachment post,
- an independent platform formed to include an aperture that receives the attachment post and engages a substantially radially-inwardly facing surface of the airfoil to block radially-outward motion of the independent platform relative to the primary member, and
- a clip that interfaces with the primary member and the independent platform to fix the independent platform to the primary member and block radially-inward motion of the independent platform relative to the primary member.
A turbine blade assembly configured to be rotated about an axis to withdraw mechanical energy from gasses interacting with the turbine blade assembly, the turbine blade assembly comprising
- a primary member comprising ceramic matrix composite materials, the primary member shaped to form an airfoil and an attachment post,
- an independent platform formed to include an aperture that receives the attachment post and engages a radially-inwardly facing surface of the airfoil to block radially-outward motion of the independent platform relative to the primary member, and
- retainer blocks that engage a radially-inwardly facing surface of the independent platform to block radially-inward motion of the independent platform relative to the primary member so that the independent platform is retained in place relative to the primary member, wherein the retainer blocks are coupled to the attachment post of the primary member.
A turbine blade assembly configured to be rotated about an axis to withdraw mechanical energy from gasses interacting with the turbine blade assembly, the turbine blade assembly comprising
- a primary member comprising ceramic matrix composite materials, the primary member shaped to form an airfoil and an attachment post,
- an independent platform formed to include an aperture that receives the attachment post and engages a substantially radially-inwardly facing surface of the airfoil to block radially-outward motion of the independent platform relative to the primary member, and
- a braze layer that interfaces with the primary member and the independent platform to fix the independent platform to the primary member and block radially-inward motion of the independent platform relative to the primary member.
Dependencies are inferred from the claim text.