# US 2019/0170013 A1 · Discontinuous Molded Tape Wear Interface for Composite Components > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0170013 A1 - Document ID: US20190170013A1 - Status: Published application - Kind: A1 - Application number: 15/833,201 - Filed: 2017-12-06 - Published: 2019-06-06 - Earliest claimed: 2017-12-06 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Christopher Paul Tura - Web page: https://patentgrep.com/patent/US20190170013A1 ## CPC - C04B 35/80: Fibres, filaments, whiskers, platelets, or the like - B32B 3/08: characterised by added members at particular parts {(layer formed of separate pieces of material which are juxtaposed side-by-side B32B3/14, B32B3/18)} - B32B 3/10: characterised by a discontinuous layer, i.e. formed of separate pieces of material - B32B 5/12: characterised by the relative arrangement of fibres or filaments of {different layers, e.g. the fibres or filaments being parallel or perpendicular to each other} - B32B 5/26: another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} - B32B 18/00: Layered products essentially comprising ceramics, e.g. refractory products - C04B 35/573: obtained by reaction sintering {or recrystallisation} - C04B 35/71: Ceramic products containing macroscopic reinforcing agents (C04B35/66 takes precedence {; infiltration of a porous ceramic matrix with a material forming a non-ceramic phase C04B41/00, reaction infiltration with Si in order to form SiC C04B35/573, in order to form Si3N4 C04B35/591}) - C04B 37/001: {directly with other burned ceramic articles} - C04B 41/009: {characterised by the material treated} - C04B 41/50: with inorganic materials - C04B 41/87: Ceramics - F01D 25/005: {Selecting particular materials} - F01D 25/246: {Fastening of diaphragms or stator-rings} - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - B32B 2260/023: Two or more layers - B32B 2260/04: Impregnation, embedding, or binder material - B32B 2260/046: Synthetic resin - B32B 2262/105: Ceramic fibres - B32B 2262/106: Carbon fibres, e.g. graphite fibres - B32B 2605/18: Aircraft - C04B 2235/5244: Silicon carbide - C04B 2235/5268: Orientation of the fibers - C04B 2237/38: Fiber or whisker reinforced - C04B 2237/584: the different additives being fibers or whiskers - C04B 2237/61: Joining two substrates of which at least one is porous by infiltrating the porous substrate with a liquid, such as a molten metal, causing bonding of the two substrates, e.g. joining two porous carbon substrates by infiltrating with molten silicon - F01D 5/288: {Protective coatings for blades} - F01D 9/04: forming ring or sector - F05D 2220/32: in gas turbines - F05D 2230/30: with deposition of material - F05D 2240/11: Shroud seal segments - F05D 2260/941: particularly aimed at mechanical or thermal stress reduction - F05D 2300/6033: Ceramic matrix composites [CMC] - F05D 2300/702: Reinforcement - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - 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 Composite components that include features that provide improved wear characteristics at the interface between the composite component and a second component are provided. As one example, a composite component can include an integrally formed discontinuous molded tape (DMT) that defines a wear interface between the component and a second component. The wear interface defined by the DMT may provide improved durability of the composite component and may facilitate more uniform wear at the interface, among other benefits. Methods for manufacturing composite components having discontinuous molded tape wear interfaces are also provided. ## Claims ### Claim 1 A component for a gas turbine engine, the component comprising: a structural laminate formed of a plurality of plies comprised of reinforcement fibers embedded within a matrix material; and a discontinuous molded tape (DMT) attached to the structural laminate and comprising a plurality of reinforcement fragments embedded within a matrix material, wherein the DMT defines a wear interface. ### Claim 2 (depends on 1) The component of claim 1, wherein the DMT is integrally formed with the structural laminate. ### Claim 3 (depends on 1) The component of claim 1, wherein the plurality of plies are unidirectional plies. ### Claim 4 (depends on 1) The component of claim 1, wherein a second component is configured to interface with the wear interface of the component. ### Claim 5 (depends on 4) The component of claim 4, wherein the structural laminate comprises one or more surfaces that define an opening, and wherein the wear interface defined by the DMT is integrally formed with the one or more surfaces of the structural laminate and further defines the opening, and wherein when the second component interfaces with the wear interface, the second component interfaces with the wear interface within the opening. ### Claim 6 (depends on 5) The component of claim 5, wherein the component is a shroud and the structural laminate is a flange of the shroud, and wherein the second component is a pin formed of a metallic material. ### Claim 7 (depends on 5) The component of claim 5, wherein the opening has a depth extending between a first end and a second end, and wherein the wear interface defined by the DMT extends between a first side and a second side along at least a portion of the depth of the opening, and wherein the wear interface defines a midline between the first side and the second side, and wherein the wear interface has a thickness extending between the one or more surfaces of the structural laminate and a wear surface of the wear interface, and wherein the thickness of the wear interface is greater proximate at least one of the first side and the second side than the thickness proximate the midline. ### Claim 8 (depends on 1) The component of claim 1, wherein a second component is configured to interface with the wear interface of the component, and wherein the component is a combustion liner and the wear interface defined by the DMT is integrally formed with one or more surfaces of the laminate structure of the combustion liner, and wherein the interface member is a ring formed of a metallic material. ### Claim 9 A method for manufacturing a composite component, the method comprising: laying up one or more plies to form a structural laminate, the one or more plies comprised of reinforcement fibers embedded within a matrix material; and attaching a discontinuous molded tape (DMT) to the structural laminate, the DMT comprised of a plurality of reinforcement fragments embedded within a matrix material, wherein the DMT defines a wear interface. ### Claim 10 (depends on 9) The method of claim 9, wherein attaching comprises piping or puttying the DMT along one or more surfaces of the structural laminate to form a desired shape of the wear interface, and wherein when the DMT is piped or puttied along the one or more surfaces, the DMT is in a paste form. ### Claim 11 (depends on 10) The method of claim 10, wherein after attaching the DMT to the structural laminate, the method further comprises: subjecting the structural laminate and the DMT to elevated temperatures and pressures in an autoclave. ### Claim 12 (depends on 9) The method of claim 9, wherein the method further comprises: subjecting the structural laminate to elevated temperatures and pressures in an autoclave; wherein, after subjecting, attaching the DMT to the structural laminate comprises nesting the DMT along one or more surfaces of the structural laminate, and wherein when the DMT is nested along the one or more surfaces of the structural laminate, the DMT is a prefabricated member in a solid form. ### Claim 13 (depends on 12) The method of claim 12, wherein nesting comprises: drawing a vacuum to drive or pull the prefabricated member along the one or more surfaces of the structural laminate such that the prefabricated member is drawn into contact with the reinforcement material; and subjecting the structural laminate and the prefabricated member to elevated temperatures and pressures in the autoclave. ### Claim 14 (depends on 13) The method of claim 13, wherein the matrix material of the prefabricated member is formed of a ceramic matrix material, and wherein when the prefabricated member is nested along the one or more surfaces of the structural laminate, the prefabricated member is a green state prefabricated member. ### Claim 15 (depends on 9) The method of claim 9, wherein the method further comprises: curing the structural laminate and the DMT so as to integrally form the DMT with the structural laminate. ### Claim 16 (depends on 15) The method of claim 15, wherein curing comprises: burning out the laminate and the DMT; and melt-infiltrating the structural laminate and the DMT so as to integrally form the DMT with the structural laminate. ### Claim 17 (depends on 9) The method of claim 9, wherein, after laying up, the method further comprises: machining an opening into the structural laminate, wherein the opening machined into the structural laminate is defined by one or more surfaces of the structural laminate, and wherein the opening has a depth extending between a first end and a second end; wherein, during attaching, the DMT is applied to the one or more surfaces of the structural laminate to further define the opening and such that the wear interface extends between a first side and a second side along at least a portion of the depth of the opening, and wherein a midline is defined between the first side and the second side, and wherein the wear interface has a thickness extending between the one or more surfaces of the structural laminate and a wear surface of the wear interface, and wherein the thickness of the wear interface is greater proximate at least one of the first side and the second side than the thickness of the wear interface proximate the midline. ### Claim 18 (depends on 9) The method of claim 9, wherein, after laying up, the method further comprises: machining an opening into the structural laminate, wherein the opening machined into the structural laminate is defined by one or more surfaces of the structural laminate, and wherein the opening has a depth extending between a first end and a second end; wherein, during attaching, the DMT is applied to the one or more surfaces of the structural laminate to further define the opening and such that the wear interface extends between a first side and a second side along at least a portion of the depth of the opening and wherein the wear interface has a thickness extending between the one or more surfaces of the structural laminate and a wear surface of the wear interface, and wherein the one or more surfaces of the structural laminate include on or more inclined surfaces that are inclined with respect to the wear surface of the wear interface. ### Claim 19 (depends on 18) The method of claim 18, and wherein the one or more inclined surfaces include a first inclined surface and a second inclined surface that converge at a tip portion. ### Claim 20 A method for manufacturing a ceramic matrix composite (CMC) component for a gas turbine engine, the CMC component comprising a structural laminate comprised of one of more unidirectional plies, the method comprising: attaching a discontinuous molded tape (DMT) to the structural laminate, the DMT comprised of a plurality of reinforcement fragments embedded within a matrix material; and curing the structural laminate and the DMT so as to integrally form the DMT with the structural laminate, wherein the DMT defines a wear interface.