# US 11,028,721 B2 · Coating to improve oxidation and corrosion resistance of abrasive tip system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,721 B2 - Document ID: US11028721B2 - Status: Granted - Kind: B2 - Application number: 16/039,907 - Filed: 2018-07-19 - Published: 2020-01-23 - Granted: 2021-06-08 - Earliest claimed: 2018-07-19 - Assignees: Ratheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Kevin Seymour; Christopher W. Strock; Thomas D. Kasprow - Web page: https://patentgrep.com/patent/US11028721B2 ## CPC - F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - B32B 5/16: characterised by features of a layer formed of particles, e.g. chips, powder {or granules (layer formed of natural mineral particles B32B19/00; layer being formed of wood fibres, chips or particles B32B21/02)} - B32B 7/05: the layers not being connected over the whole surface, e.g. discontinuous connection or patterned connection (using interposed adhesives or bonding materials applied in spaced arrangements B32B7/14) - B32B 7/12: using interposed adhesives or interposed materials with bonding properties - 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 5/288: {Protective coatings for blades} - B32B 2603/00: Vanes, blades, propellers, rotors with blades - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2230/90: Coating; Surface treatment - F05D 2240/307: related to the tip of a rotor blade - F05D 2300/20: Oxide or non-oxide ceramics - F05D 2300/506: Hardness - 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) - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - 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 An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degree Fahrenheit, comprising: a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material. ## Claims ### Claim 1 An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degrees Fahrenheit, comprising: a plurality of grit particles adapted to be placed on a top surface of said substrate; a matrix material bonded to said top surface; said matrix material partially surrounds said grit particles, wherein said grit particles extend above said matrix material relative to said top surface; and a film of oxidant resistant coating applied over said plurality of grit particles and said matrix material, wherein said film of oxidant resistant coating consists of a mixture of aluminum and zirconium oxide, and zirconium toughened aluminum oxide. ### Claim 2 (depends on 1) The abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degrees Fahrenheit according to claim 1, wherein said grit particles comprise a hard ceramic phase. ### Claim 3 (depends on 1) The abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degrees Fahrenheit according to claim 1, wherein said matrix material comprises a matrix formed from at least one of Ni, Co and MCrAlY, wherein M is Ni or Co, pure Ni and a cobalt chrome carbide material. ### Claim 4 (depends on 1) The abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degrees Fahrenheit according to claim 1, wherein said film of oxidant resistant coating comprises an oxide coating. ### Claim 5 (depends on 1) The abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degrees Fahrenheit according to claim 1, further comprising: an adhesion layer coupled to said top surface, wherein said adhesion layer is configured to adhere said grit particles to said top surface. ### Claim 6 A turbine engine component configured for a gas path of at most 500 degrees Fahrenheit comprising: an airfoil having a tip; a composite abrasive coating bonded to said tip; said composite abrasive coating comprising an adhesion layer bonded to said tip; a layer of grit particles bonded to said adhesion layer; a matrix material coupled to said adhesion layer and connected to said grit particles; and a film of oxidant resistant coating applied over said plurality of grit particles and said matrix material, wherein said film of oxidant resistant coating consists of a mixture of aluminum and zirconium oxide, and zirconium toughened aluminum oxide. ### Claim 7 (depends on 6) The turbine engine component configured for a gas path of at most 500 degrees Fahrenheit according to claim 6, wherein said first grit particles extend above said matrix material relative to said tip or said first grit particles are flush with said matrix material relative to said tip and combinations thereof. ### Claim 8 (depends on 6) The turbine engine component configured for a gas path of at most 500 degrees Fahrenheit according to claim 6, wherein said airfoil is a portion of said component configured for a gas path of at most 500 degrees Fahrenheit. ### Claim 9 (depends on 6) The turbine engine component configured for a gas path of at most 500 degrees Fahrenheit according to claim 6, wherein said film of oxidant resistant coating has a thickness from 0.0002 inch-0.002 inch. ### Claim 10 (depends on 6) The turbine engine component configured for a gas path of at most 500 degrees Fahrenheit according to claim 6, wherein said film of oxidant resistant coating is configured to protect said matrix material from oxidation. ### Claim 11 (depends on 6) The turbine engine component configured for a gas path of at most 500 degrees Fahrenheit according to claim 6, wherein said component is at least one of a fan and a low pressure compressor. ### Claim 12 A process for coating a turbine engine airfoil with an abrasive, said process comprising: applying an adhesion layer onto a tip of said airfoil, wherein said airfoil is configured to operate in a gas path having a maximum temperature of 500 degrees Fahrenheit; adhering a plurality of grit particles to said adhesion layer, wherein spaces are formed between said grit particles; applying a matrix material to said adhesion layer and connecting to said grit particles; applying a film of oxidant resistant coating over said plurality of grit particles and said matrix material, wherein said film of oxidant resistant coating consists of a mixture of aluminum and zirconium oxide, and zirconium toughened aluminum oxide. ### Claim 13 (depends on 12) The process of claim 12, wherein said film of oxidant resistant coating has a thickness from 0.0002 inch-0.002 inch. ### Claim 14 (depends on 12) The process of claim 12, wherein said first grit particles extend above said matrix material relative to said tip; or wherein said first grit particles are flush with said matrix material relative to said tip; or wherein said first grit particles are below said first grit particles relative to said tip; and combinations thereof. ### Claim 15 (depends on 14) The process of claim 14, wherein said turbine engine airfoil is part of a component in at least one of a fan and a low pressure compressor. ### Claim 16 (depends on 14) The process of claim 14, wherein said turbine engine airfoil comprises an aluminum or polymer composite material.