# US 10,767,497 B2 · Turbine vane assembly with ceramic matrix composite components > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,497 B2 - Document ID: US10767497B2 - Status: Granted - Kind: B2 - Application number: 16/124,970 - Filed: 2018-09-07 - Published: 2020-03-12 - Granted: 2020-09-08 - Earliest claimed: 2018-09-07 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce Corporation; Rolls-Royce plc - Inventors: Daniel K. Vetters; Michael J. Whittle; Eric Koenig; Jeffrey A. Walston - Web page: https://patentgrep.com/patent/US10767497B2 ## CPC - F01D 5/284: {Selection of ceramic materials} - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/005: {Selecting particular materials} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F05D 2260/30: Retaining components in desired mutual position - F05D 2260/31: Retaining bolts or nuts - F05D 2260/38: by a spring, i.e. spring loaded or biased towards a certain position - F05D 2300/50212: dissimilar - F05D 2300/6033: Ceramic matrix composites [CMC] - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The assembly of claim 1, wherein the at least one bias spring directly engages one of the outer end wall and the inner end wall of the ceramic matrix composite heat shield, and the at least one bias spring directly engages the first plate. ### Claim 3 (depends on 2) The assembly of claim 2, wherein the interface components include a plurality of bias springs that each directly engages one of the outer end wall and the inner end wall of the ceramic matrix composite heat shield, and each of the plurality of bias springs directly engages the first plate. ### Claim 4 (depends on 2) The assembly of claim 2, wherein the first plate is located radially outward of the outer end wall included in the ceramic matrix composite heat shield. ### Claim 5 (depends on 4) The assembly of claim 4, wherein the metallic support structure includes a second plate located radially inward of the inner end wall of the ceramic matrix composite heat shield, and the second plate is fixed to a radially-inner end of the spar of the metallic support structure. ### Claim 6 (depends on 5) The assembly of claim 5, wherein the second plate is formed to include at least one cooling air passage in fluid communication with an interior cavity formed by the airfoil of the ceramic matrix composite heat shield. ### Claim 7 (depends on 1) The assembly of claim 1, wherein the first collar is shaped to include a sleeve that extends into the cavity and a panel that extends outwardly away from the sleeve outside the cavity. ### Claim 8 (depends on 7) The assembly of claim 7, wherein the at least one bias spring directly engages one of the outer end wall and the inner end wall of the ceramic matrix composite heat shield, and the at least one bias spring directly engages the panel of the first collar. ### Claim 9 (depends on 7) The assembly of claim 7, wherein the first collar is formed to include cooling air passageways that extend through both the sleeve and the panel to provide fluid communication into the cavity. ### Claim 10 (depends on 7) The assembly of claim 7, wherein the interface components include a second collar that extends part-way into the cavity through the airfoil included in the ceramic matrix composite heat shield at a radially opposite end from the first collar to transfer aerodynamic loads from the airfoil to surrounding components, and the second collar is shaped to include a sleeve that extends into the cavity and a panel that extends outwardly away from the sleeve outside the cavity. ### Claim 11 (depends on 1) The assembly of claim 1, wherein the first collar is shaped to form a sleeve that extends into the cavity of the airfoil and a panel arranged outside the cavity that extends away from the sleeve. ### Claim 12 (depends on 11) The assembly of claim 11, wherein the plurality of bias springs directly engage the panel of the first collar and the first plate of the metallic support structure. ### Claim 13 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. ### Claim 14 (depends on 13) The assembly of claim 13, wherein the plurality of bias springs directly engage the at least one end wall of the ceramic matrix composite heat shield and the first plate of the metallic support structure. ### Claim 15 (depends on 14) The assembly of claim 14, wherein the metallic support structure includes a second plate coupled to the spar outside the airfoil with the airfoil and the at least one end wall of the ceramic matrix composite heat shield located radially between the first plate and the second plate of the metallic support structure. ### Claim 16 (depends on 15) The assembly of claim 15, wherein the at least one end wall of the ceramic matrix composite heat shield includes a first end wall and a second end wall, the first end wall arranged radially between the first plate of the metallic support structure and the primary gas path, and the second end wall arranged radially between the second plate of the metallic support structure and the primary gas path. ### Claim 17 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. ### Claim 18 (depends on 17) The assembly of claim 17, wherein the bias member is co-axial with the spar of the metallic support structure.