# US 2014/0193270 A1 · Ceramic composite matrix material bonded assembly and processes thereof > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0193270 A1 - Document ID: US20140193270A1 - Status: Published application - Kind: A1 - Application number: 13/736,723 - Filed: 2013-01-08 - Published: 2014-07-10 - Earliest claimed: 2013-01-08 - Assignees: COI Ceramics, Inc. - Applicants: COI Ceramics, Inc. - Inventors: Richard B. Plunkett; Kourtney R. Buckley; Andrew Szweda - Web page: https://patentgrep.com/patent/US20140193270A1 ## CPC - B29D 99/0025: {Producing blades or the like, e.g. blades for turbines, propellers, or wings} - C04B 37/005: {consisting of glass or ceramic material} - 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 5/28: Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion - 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)} - C04B 2235/483: Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes - C04B 2235/5252: having a specific pre-form - C04B 2235/5256: Two-dimensional, e.g. woven structures - C04B 2235/5268: Orientation of the fibers - C04B 2235/616: Liquid infiltration of green bodies or pre-forms - C04B 2237/08: Non-oxidic interlayers - C04B 2237/38: Fiber or whisker reinforced - C04B 2237/80: Joining the largest surface of one substrate with a smaller surface of the other substrate, e.g. butt joining or forming a T-joint - C04B 2237/84: Joining of a first substrate with a second substrate at least partially inside the first substrate, where the bonding area is at the inside of the first substrate, e.g. one tube inside another tube - B29D: PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE (making granules B29B9/00; making preforms B29B11/00) - C04B: LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE {(roofing granules E04D7/005)}; CERAMICS (devitrified glass-ceramics C03C10/00); REFRACTORIES; TREATMENT OF NATURAL STONE - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## Abstract A method of making multipart assemblies by producing single parts from ceramic composite materials that are machined and bonded together to form the multipart assembly. The method is used to make turbine engine vanes. ## Claims ### Claim 1 A method of fabricating a multi-part assembly comprising applying a ceramic precursor to at least a portion of at least one of a first part and second parts; converting the ceramic precursor into a ceramic to bond the at least first part to the second part. ### Claim 2 (depends on 1) The method of claim 1, further comprising forming the at least first part and the at least second parts. ### Claim 3 (depends on 1) The method of claim 1, wherein the forming the at least one of the first part and second part further comprises using impregnated material to form the at least one of the first part and second part. ### Claim 4 (depends on 1) The method of claim 1, wherein the forming of at least one of the first part and second part is from a ceramic matrix composite. ### Claim 5 (depends on 1) The method of claim 1, wherein the forming of at least one of the first part and second part is from a 2-D or 3D woven preform or combinations thereof. ### Claim 6 (depends on 1) The method of claim 1, wherein the forming of at least one of the first part and second part is from a non-oxide ceramic matrix composite. ### Claim 7 (depends on 1) The method of claim 1, wherein at least one of the first and second part has a cross-sectional geometry that varies along the length, wherein at least one of the first part and second part has continuous fibers. ### Claim 8 (depends on 1) The method of claim 1, wherein the ceramic precursor is at least one of polysilazanes, hydridopolysilazanes, polysiloxanes or borosilizanes. ### Claim 9 (depends on 1) The method of claim 1, wherein the applying the ceramic precursor to the at least one of the first part and second part further comprises applying the ceramic precursor to a faying surface of the part to be bonded. ### Claim 10 (depends on 1) The method of claim 1, wherein the applying is by infiltrating the ceramic precursor into the parts. ### Claim 11 (depends on 1) The method of claim 1, wherein the converting the ceramic precursor is by pyrolysis. ### Claim 12 (depends on 1) The method of claim 1, further comprising forming at least a portion of a turbine vane with the at least one first part and the at least one second part. ### Claim 13 A method of forming a turbine vane comprising: forming an airfoil; forming a first platform; forming a second platform; applying a ceramic precursor to the airfoil between the first and second platform; and converting the ceramic precursor into a ceramic to bond the airfoil between the at least first and second platforms. ### Claim 14 (depends on 13) The method of claim 13, wherein the forming is from a ceramic composite material. ### Claim 15 (depends on 13) The method of claim 13 wherein the vane comprises a plurality of airfoils disposed between the first and second platforms. ### Claim 16 A turbine vane assembly comprising: an airfoil; a first platform; a second platform; and a ceramic bond coupling the airfoil nested between the two platforms. ### Claim 17 (depends on 16) The assembly of claim 16 wherein the airfoil, first and second platform are a ceramic matrix composite. ### Claim 18 (depends on 16) The assembly of claim 16, wherein the airfoil is hollow or solid member. ### Claim 19 (depends on 16) The assembly of claim 16, wherein the assembly comprises a plurality of airfoils nested between the first and second platforms.