# US 10,767,496 B2 · Turbine blade assembly with mounted platform > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,496 B2 - Document ID: US10767496B2 - Status: Granted - Kind: B2 - Application number: 15/934,350 - Filed: 2018-03-23 - Published: 2019-09-26 - Granted: 2020-09-08 - Earliest claimed: 2018-03-23 - Assignees: Rolls-Royce North American Technologies Inc.; ROLLS-ROYCE plc - Applicants: Rolls-Royce North American Technologies Inc.; Rolls-Royce Corporation - Inventors: Ted J. Freeman; Michael A. Kowalkowski - Web page: https://patentgrep.com/patent/US10767496B2 ## CPC - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments} - F01D 5/284: {Selection of ceramic materials} - F01D 5/3007: {of axial insertion type} - F01D 5/3084: {the blades being made of ceramics} - F01D 11/008: {by spacer elements between the blades, e.g. independent interblade platforms} - F05D 2230/21: by casting - F05D 2230/237: Brazing - F05D 2240/80: Platforms for stationary or moving blades - F05D 2260/36: by a form fit connection, e.g. by interlocking - 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 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. ## Claims ### Claim 1 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, 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, and retainer blocks that engage a radially inner-most facing surface of the independent platform to block radially-inward motion of the independent platform relative to the primary member of the turbine blade assembly. ### Claim 2 (depends on 1) The turbine blade assembly of claim 1, wherein the retainer blocks are coupled to the attachment post of the primary member. ### Claim 3 (depends on 1) The turbine blade assembly of claim 1, wherein the retainer blocks are shaped to provide a root of the turbine blade assembly configured to engage with a slot formed in a corresponding turbine disk. ### Claim 4 (depends on 1) The turbine blade assembly of claim 1, wherein the retainer blocks are formed to include recesses, each of the recesses positioned to receive a portion of the attachment post of the primary member. ### Claim 5 (depends on 4) The turbine blade assembly of claim 4, wherein the retainer blocks are fixed to one another and the recesses formed in the retainer blocks are shaped so as to block removal of the attachment post from the root provided by the retainer blocks. ### Claim 6 (depends on 5) The turbine blade assembly of claim 5, wherein the retainer blocks are fixed to one another by a diffusion braze or diffusion bond. ### Claim 7 (depends on 1) The turbine blade assembly of claim 1, wherein the clip is a bi-cast component that interfaces with the attachment post of the primary member included in the turbine blade assembly. ### Claim 8 (depends on 7) The turbine blade assembly of claim 7, wherein the attachment post of the primary member is shaped to provide a root of the turbine blade assembly configured to engage with a slot formed in a corresponding turbine disk. ### Claim 9 (depends on 1) The turbine blade assembly of claim 1, wherein the clip is a bi-cast component and interfaces with the airfoil of the primary member included in the turbine blade assembly. ### Claim 10 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 inner-most 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. ### Claim 11 (depends on 10) The turbine blade assembly of claim 10, wherein the independent platform is coupled to the attachment post by a clip that interfaces between the independent platform and the attachment post of the primary member to fix the independent platform in place relative to the primary member of the turbine blade assembly. ### Claim 12 (depends on 10) The turbine blade assembly of claim 10, wherein the retainer blocks are shaped to provide a root of the turbine blade assembly configured to engage with a slot formed in a corresponding turbine disk. ### Claim 13 (depends on 12) The turbine blade assembly of claim 12, wherein the retainer blocks are formed to include recesses, each of the recesses positioned to receive a portion of the attachment post of the primary member. ### Claim 14 (depends on 13) The turbine blade assembly of claim 13, wherein the retainer blocks are fixed to one another and the recesses formed in the retainer blocks are shaped so as to block removal of the attachment post from the root provided by the retainer blocks. ### Claim 15 (depends on 14) The turbine blade assembly of claim 14, wherein the retainer blocks are fixed to one another by a diffusion braze or diffusion bond. ### Claim 16 (depends on 10) The turbine blade assembly of claim 10, wherein the retainer blocks extend around only a portion of the attachment post adjacent to the independent platform to form a keeper collar and the attachment post is shaped to provide a root of the turbine blade assembly configured to engage with a slot formed in a corresponding turbine disk. ### Claim 17 (depends on 16) The turbine blade assembly of claim 16, wherein the attachment post has a dovetail shape configured to engage with a dovetail slot formed in a corresponding turbine disk. ### Claim 18 (depends on 16) The turbine blade assembly of claim 16, wherein the retainer blocks of the keeper collar are fixed to the attachment post by at least one bi-cast clip. ### Claim 19 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, 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, and retainer blocks that engage a radially inner-most surface of the independent platform to block radially-inward motion of the independent platform relative to the primary member.