Patents by Inventor Andrew Joseph Lazur
Andrew Joseph Lazur has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20170073277Abstract: In some examples, a method may include depositing, from a slurry comprising particles including silicon metal, a bond coat precursor layer including the particles comprising silicon metal directly on a ceramic matrix composite substrate. The method also may include locally heating the bond coat precursor layer to form a bond coat comprising silicon metal. Additionally, the method may include forming a protective coating on the bond coat. In some examples, an article may include a ceramic matrix composite substrate, a bond coat directly on the substrate, and a protective coating on the bond coat. The bond coat may include silicon metal and a metal comprising at least one of Zr, Y, Yb, Hf, Ti, Al, Cr, Mo, Nb, Ta, or a rare earth metal.Type: ApplicationFiled: September 9, 2016Publication date: March 16, 2017Inventors: Sungbo Shim, Kang N. Lee, Stephen Isaiah Harris, Andrew Joseph Lazur
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Publication number: 20170073820Abstract: An apparatus includes a ceramic matrix composite (CMC) component and an interface coating on the CMC component, wherein the interface coating includes a layer of at least one of the following compositions: 40-50 wt % Nb, 28-42 wt % Al, 4-15 wt % Cr, 1-2 wt % Si; 90-92 wt % Mo, 4-5 wt % Si, 4-5 wt % B; or 60-80 wt % V, 20-30 wt % Cr, 2-15 wt % Ti.Type: ApplicationFiled: November 22, 2016Publication date: March 16, 2017Inventors: Adam Lee Chamberlain, Kang N. Lee, Andrew Joseph Lazur
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Patent number: 9573354Abstract: A method including applying layers of multiple constituents where the constituents are capable of producing a non-equilibrium condition on the contacting surfaces of a ceramic matrix composite component and a gas turbine engine component where one outer coating includes a first constituent and the other outer coating includes a second constituent; forming a component assembly with the ceramic matrix composite component coupled to the gas turbine engine component with contact between the outer coatings; adding an energy to facilitate an equilibrium reaction between the first constituent of the first outer coating and the second constituent of the second outer coating; and as a result of adding the energy, forming a bond structure in the component assembly with a product of the equilibrium reaction where the bond structure affixes the ceramic matrix composite component to the gas turbine engine component between the first constituent and the second constituent.Type: GrantFiled: December 5, 2013Date of Patent: February 21, 2017Assignee: Rolls-Royce CorporationInventors: Adam Lee Chamberlain, Andrew Joseph Lazur
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Patent number: 9556743Abstract: In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer.Type: GrantFiled: July 1, 2015Date of Patent: January 31, 2017Assignee: Rolls-Royce CorporationInventors: Adam Lee Chamberlain, Andrew Joseph Lazur, Kang N. Lee
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Patent number: 9527777Abstract: An apparatus includes a ceramic matrix composite (CMC) component and an interface coating on the CMC component, wherein the interface coating includes a layer of at least one of the following compositions: 100 wt % Ir; 90-95 wt % Ir, 5-10 wt % Co, 1-2 wt % Al, 1-2 wt % Si; 40-50 wt % Nb, 28-42 wt % Al, 4-15 wt % Cr, 1-2 wt % Si; 90-92 wt % Mo, 4-5 wt % Si, 4-5 wt % B; or 60-80 wt % V, 20-30 wt % Cr, 2-15 wt % Ti.Type: GrantFiled: March 11, 2014Date of Patent: December 27, 2016Assignee: ROLLS-ROYCE CORPORATIONInventors: Adam Lee Chamberlain, Kang N. Lee, Andrew Joseph Lazur
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Patent number: 9387512Abstract: In some examples, a method includes identifying a damaged area in a ceramic matrix composite coating of an in-service component; applying a restoration slurry to the damaged area of the ceramic matrix composite coating, wherein the restoration slurry comprises a liquid carrier and a restoration coating material; drying the restoration slurry to form a dried restoration slurry; and heat treating the dried restoration slurry to form a restored portion of the ceramic matrix composite coating. In some examples, an assembly may include a component including a substrate and a coating on the substrate, where the coating defines a damaged portion; masking around the damaged portion on undamaged portions of the coating; and a restoration slurry in the damaged portion, wherein the restoration slurry comprises a liquid carrier and a restoration coating material.Type: GrantFiled: March 14, 2014Date of Patent: July 12, 2016Assignee: Rolls-Royce CorporationInventors: Kang N. Lee, Adam Lee Chamberlain, Andrew Joseph Lazur
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Publication number: 20160146028Abstract: A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.Type: ApplicationFiled: January 29, 2016Publication date: May 26, 2016Inventor: Andrew Joseph Lazur
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Publication number: 20160137559Abstract: An apparatus includes a ceramic matrix composite (CMC) component and an interface coating on the CMC component, wherein the interface coating includes a layer of at least one of the following compositions: 100 wt % Ir; 90-95 wt % Ir, 5-10 wt % Co, 1-2 wt % Al, 1-2 wt % Si; 40-50 wt % Nb, 28-42 wt % Al, 4-15 wt % Cr, 1-2 wt % Si; 90-92 wt % Mo, 4-5 wt % Si, 4-5 wt % B; or 60-80 wt % V, 20-30 wt % Cr, 2-15 wt % Ti.Type: ApplicationFiled: March 11, 2014Publication date: May 19, 2016Applicant: Rolls-Royce CorporationInventors: Adam Lee Chamberlain, Kang N. Lee, Andrew Joseph Lazur
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Patent number: 9328620Abstract: A method for making a gas turbine engine matrix composite structure. The method includes providing at least one metal core element, fabricating a matrix composite component about the metal core element, and removing at least part of the metal core element from the matrix composite component by introduction of a halogen gas.Type: GrantFiled: December 27, 2013Date of Patent: May 3, 2016Assignee: Rolls-Royce CorporationInventors: Andrew Joseph Lazur, Adam Lee Chamberlain
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Patent number: 9291060Abstract: A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.Type: GrantFiled: December 5, 2013Date of Patent: March 22, 2016Assignee: Rolls-Royce CorporationInventor: Andrew Joseph Lazur
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Publication number: 20160003092Abstract: In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer.Type: ApplicationFiled: July 1, 2015Publication date: January 7, 2016Inventors: Adam Lee Chamberlain, Andrew Joseph Lazur, Kang N. Lee
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Publication number: 20140272431Abstract: A method including applying layers of multiple constituents where the constituents are capable of producing a non-equilibrium condition on the contacting surfaces of a ceramic matrix composite component and a gas turbine engine component where one outer coating includes a first constituent and the other outer coating includes a second constituent; forming a component assembly with the ceramic matrix composite component coupled to the gas turbine engine component with contact between the outer coatings; adding an energy to facilitate an equilibrium reaction between the first constituent of the first outer coating and the second constituent of the second outer coating; and as a result of adding the energy, forming a bond structure in the component assembly with a product of the equilibrium reaction where the bond structure affixes the ceramic matrix composite component to the gas turbine engine component between the first constituent and the second constituent.Type: ApplicationFiled: December 5, 2013Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventors: Adam Lee Chamberlain, Andrew Joseph Lazur
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Publication number: 20140272249Abstract: In some examples, a method includes identifying a damaged area in a ceramic matrix composite coating of an in-service component; applying a restoration slurry to the damaged area of the ceramic matrix composite coating, wherein the restoration slurry comprises a liquid carrier and a restoration coating material; drying the restoration slurry to form a dried restoration slurry; and heat treating the dried restoration slurry to form a restored portion of the ceramic matrix composite coating. In some examples, an assembly may include a component including a substrate and a coating on the substrate, where the coating defines a damaged portion; masking around the damaged portion on undamaged portions of the coating; and a restoration slurry in the damaged portion, wherein the restoration slurry comprises a liquid carrier and a restoration coating material.Type: ApplicationFiled: March 14, 2014Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventors: Kang N. Lee, Adam Lee Chamberlain, Andrew Joseph Lazur
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Publication number: 20140271161Abstract: A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.Type: ApplicationFiled: December 5, 2013Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventor: Andrew Joseph Lazur
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Publication number: 20140272274Abstract: A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.Type: ApplicationFiled: December 5, 2013Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventor: Andrew Joseph Lazur
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Publication number: 20140272246Abstract: Techniques for joining textile materials are provided. In one non-limiting form, a system includes a woven structure having a first woven layer and at least a first section and a second section. The first section includes a first fringe portion and a first set of fibers, and the second section includes a second fringe portion and a second set of fibers. The fibers of the first and second sets of fibers are configured in the first and second fringe portions to provide an interlocking arrangement between the first and second sections. Further embodiments, forms, features, and aspects shall become apparent from the description and drawings.Type: ApplicationFiled: December 27, 2013Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventor: Andrew Joseph Lazur
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Publication number: 20140272310Abstract: In one example, article comprising a substrate defining an outer surface; a plurality of joint conduits formed in the outer surface of the substrate, wherein each conduit of the plurality of joint conduits exhibits an undercut configuration; and a coating formed on the outer surface of the substrate, wherein the coating substantially fills the plurality of joint conduits formed in the surface of the substrate.Type: ApplicationFiled: March 14, 2014Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventors: Andrew Joseph Lazur, Kang N. Lee, Adam Lee Chamberlain
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Publication number: 20140261986Abstract: A method for making a gas turbine engine matrix composite structure. The method includes providing at least one metal core element, fabricating a matrix composite component about the metal core element, and removing at least part of the metal core element from the matrix composite component by introduction of a halogen gas.Type: ApplicationFiled: December 27, 2013Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventors: Andrew Joseph Lazur, Adam Lee Chamberlain