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US 10,767,497 B2Granted
Turbine vane assembly with ceramic matrix composite components
AssigneeROLLS-ROYCE plc
InventorsDaniel K. Vetters, Michael J. Whittle, Eric Koenig, Jeffrey A. Walston
Life of this patent
Estimating the term…
Abstract
Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.
Claims18
A turbine vane assembly, the assembly comprising
- a ceramic matrix composite heat shield adapted to withstand high temperatures, the ceramic matrix composite heat shield shaped to include an inner end wall, an outer end wall spaced in a radial direction from the inner end wall to define a primary gas path therebetween, and an airfoil that extends from the inner end wall to the outer end wall,
- a metallic support structure that extends radially through the ceramic matrix composite heat shield, the metallic support structure including a first plate arranged radially inward or radially outward of the ceramic matrix composite heat shield and a spar that extends radially from the first plate through the ceramic matrix composite heat shield, and
- interface components configured to interconnect and to allow for differing rates of thermal expansion between the ceramic matrix composite heat shield and the metallic support structure, the interface components including at least one bias spring arranged radially between the ceramic matrix composite heat shield and the first plate of the metallic support structure,
- wherein the interface components include a first collar that extends part-way into a cavity though the airfoil included in the ceramic matrix composite heat shield to transfer aerodynamic loads from the airfoil to surrounding components.
1 more element
A turbine vane assembly, the assembly comprising
- a ceramic matrix composite heat shield including an airfoil that extends radially across a primary gas path and at least one end wall that defines a radial boundary of the primary gas path,
- a metallic support structure including a spar that extends radially through the airfoil and a first plate fixed to the spar outside the airfoil,
- a plurality of bias springs arranged radially between the at least one end wall of the ceramic matrix composite heat shield and the first plate of the metallic support structure, and
- a first collar that extends partway into a cavity that extends radially through the airfoil around the spar and that contacts an interior side of the airfoil.
1 more element
A turbine vane assembly, the assembly comprising
- a ceramic matrix composite heat shield, the heat shield including an airfoil shaped to define a cavity extending radially through the airfoil,
- a metallic support structure including a spar that extends through the cavity of the airfoil and a plate fixed to the spar outside the cavity, the plate sized and arranged so as not to fit through the cavity, and
- interface components configured to that interconnect the ceramic matrix composite heat shield with the metallic support structure, the interface components including a first collar arranged radially between the plate of the metallic support structure and the ceramic matrix composite heat shield, a second collar arranged so that the ceramic matrix composite heat shield is radially between the first collar and the second collar, and a bias member that extends from the first collar to the second collar through the cavity of the airfoil included in the ceramic matrix composite airfoil.
Dependencies are inferred from the claim text.