Patents by Inventor Andres Jose Garcia Crespo
Andres Jose Garcia Crespo 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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Patent number: 10738644Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.Type: GrantFiled: August 30, 2017Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
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Patent number: 10633985Abstract: A system includes a blade segment having a blade and a mounting segment coupled to the blade. Additionally, the mounting segment includes a first contact face and a second contact face, wherein the first and second contact face are concave with respect to a longitudinal axis of the blade segment. To reduce stresses within the mounting segment, the mounting segment further includes a lower face coupling the first contact face and the second contact face, wherein the lower face is convex across the longitudinal axis of the blade segment.Type: GrantFiled: June 25, 2012Date of Patent: April 28, 2020Assignee: General Electric CompanyInventors: Andrés Jose Garcia-Crespo, Patrick Daniel Noble
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Patent number: 10465533Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.Type: GrantFiled: October 8, 2015Date of Patent: November 5, 2019Assignee: General Electric CompanyInventors: Victor John Morgan, Jacob John Kittleson, Andres Jose Garcia-Crespo, Benjamin Paul Lacy
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Patent number: 10352170Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The turbine rotor blade airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: May 2, 2017Date of Patent: July 16, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: John Franklin Ryman, Xiaoyong Fu, Andres Jose Garcia-Crespo, Ross J. Gustafson
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Publication number: 20190063250Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
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Patent number: 10215036Abstract: An assembly and method for affixing a turbomachine rotor blade to a rotor wheel are disclosed. In an embodiment, an adaptor member is provided disposed between the blade and the rotor wheel, the adaptor member including an adaptor attachment slot that is complementary to the blade attachment member, and an adaptor attachment member that is complementary to the rotor wheel attachment slot. A coverplate is provided, having a coverplate attachment member that is complementary to the rotor wheel attachment slot, and a hook for engaging the adaptor member. When assembled, the coverplate member matingly engages with the adaptor member, and retains the blade in the adaptor member, and the assembly in the rotor wheel.Type: GrantFiled: March 31, 2016Date of Patent: February 26, 2019Assignee: General Electric CompanyInventors: Andres Jose Garcia-Crespo, John McConnell Delvaux, Diane Patricia Miller
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Publication number: 20180355725Abstract: A method of creating a cooling arrangement for a turbine component, and a cooling arrangement are provided. The turbine component includes an interior cooling passage formed therein. The method comprises a step of forming a slot through a sidewall of the turbine component. The method further comprises a step of forming an insert having one or more cooling features and a cavity. The method further comprises a step of positioning the insert within the slot. The method further comprises a step of securing the insert within the slot. The method further comprises a step of forming at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.Type: ApplicationFiled: June 13, 2017Publication date: December 13, 2018Inventors: Victor John MORGAN, Andres Jose GARCIA-CRESPO, Elisabeth Kraus BLACK, George Andrew GERGELY, Jonathan Glenn REED
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Patent number: 10132170Abstract: A system includes a turbomachine blade segment including an airfoil with an exterior surface, and a platform coupled to the airfoil having a first side and a second side. The system also includes a concave fillet transition extending between the airfoil and the platform. The concave fillet transition includes one or more interface ply segments extending across the exterior surface of the airfoil and the first or the second side of the platform to form a continuous surface between the airfoil and the platform.Type: GrantFiled: March 15, 2013Date of Patent: November 20, 2018Assignee: General Electric CompanyInventors: Andres Jose Garcia-Crespo, Peter de Diego
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Publication number: 20180320526Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The turbine rotor blade airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: May 2, 2017Publication date: November 8, 2018Inventors: John Franklin Ryman, Xiaoyong Fu, Andres Jose Garcia-Crespo, Ross J. Gustafson
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Patent number: 9718735Abstract: Components are disclosed which include a CMC substrate having a first surface and a second surface. The first surface is in fluid communication with a compressed, dry fluid, and the second surface is in fluid communication with a wet fluid stream and includes a hermetic coating. The components further include at least one opening extending from the first surface through a portion of the CMC substrate, wherein, upon removal of a fragment of one or both of the hermetic coating and the CMC substrate, the at least one opening selectively permits a flow of the compressed, dry fluid to the second surface. In one embodiment, the component is a gas turbine component, the wet fluid stream is a hot combustion stream, the hermetic coating is an environmental barrier coating, and the flow reduces or eliminates volatilization of the CMC substrate. Methods for forming the components are also disclosed.Type: GrantFiled: February 3, 2015Date of Patent: August 1, 2017Assignee: General Electric CompanyInventors: John McConnell Delvaux, Andres Jose Garcia-Crespo, Victor John Morgan, Jacob John Kittleson
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Patent number: 9664056Abstract: A turbine system and adapter are disclosed. The adapter includes a turbine attachment portion having a first geometry arranged to receive a corresponding geometry of a wheelpost of a turbine rotor, and a bucket attachment portion having a second geometry arranged to receive a corresponding geometry of a root portion of a non-metallic turbine bucket. Another adapter includes a turbine attachment portion arranged to receive a plurality of wheelposts of a turbine rotor, and a bucket attachment portion arranged to receive a plurality of non-metallic turbine buckets having single dovetail configuration root portions. The turbine system includes a turbine rotor wheel configured to receive metal buckets, at least one adapter secured to at least one wheelpost on the turbine rotor wheel, and at least one non-metallic bucket secured to the at least one adapter.Type: GrantFiled: August 23, 2013Date of Patent: May 30, 2017Assignee: General Electric CompanyInventors: Nicholas Alvin Hogberg, Andres Jose Garcia-Crespo
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Publication number: 20170101873Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.Type: ApplicationFiled: October 8, 2015Publication date: April 13, 2017Inventors: Victor John MORGAN, Jacob John KITTLESON, Andres Jose GARCIA-CRESPO, Benjamin Paul LACY
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Patent number: 9482108Abstract: Embodiments of the present disclosure include a system comprising a turbomachine blade assembly having a blade portion, a shank portion, and a mounting portion, wherein the blade portion, the shank portion, and the mounting portion comprise a first plurality of plies extending from a tip of the airfoil to a base of the dovetail.Type: GrantFiled: April 3, 2013Date of Patent: November 1, 2016Assignee: General Electric CompanyInventor: Andres Jose Garcia Crespo
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Patent number: 9435209Abstract: Embodiments of the present disclosure include a system having a turbomachine blade segment including a blade and a mounting segment coupled to the blade, wherein the mounting segment has a plurality of reinforcement pins laterally extending at least partially through a neck of the mounting segment.Type: GrantFiled: October 25, 2012Date of Patent: September 6, 2016Assignee: General Electric CompanyInventor: Andres Jose Garcia Crespo
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Patent number: 9435268Abstract: A method of controlling volatilization of silicon based components in a gas turbine engine includes measuring, estimating and/or predicting a variable related to operation of the gas turbine engine; correlating the variable to determine an amount of silicon to control volatilization of the silicon based components in the gas turbine engine; and injecting silicon into the gas turbine engine to control volatilization of the silicon based components. A gas turbine with a compressor, combustion system, turbine section and silicon injection system may be controlled by a controller that implements the control method.Type: GrantFiled: March 24, 2014Date of Patent: September 6, 2016Assignee: General Electric CompanyInventors: Andres Jose Garcia-Crespo, John Delvaux, Noemie Dion Ouellet
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Publication number: 20160221881Abstract: Components are disclosed which include a CMC substrate having a first surface and a second surface. The first surface is in fluid communication with a compressed, dry fluid, and the second surface is in fluid communication with a wet fluid stream and includes a hermetic coating. The components further include at least one opening extending from the first surface through a portion of the CMC substrate, wherein, upon removal of a fragment of one or both of the hermetic coating and the CMC substrate, the at least one opening selectively permits a flow of the compressed, dry fluid to the second surface. In one embodiment, the component is a gas turbine component, the wet fluid stream is a hot combustion stream, the hermetic coating is an environmental barrier coating, and the flow reduces or eliminates volatilization of the CMC substrate. Methods for forming the components are also disclosed.Type: ApplicationFiled: February 3, 2015Publication date: August 4, 2016Inventors: John McConnell DELVAUX, Andres Jose GARCIA-CRESPO, Victor John MORGAN, Jacob John KITTLESON
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Publication number: 20160208625Abstract: An assembly and method for affixing a turbomachine rotor blade to a rotor wheel are disclosed. In an embodiment, an adaptor member is provided disposed between the blade and the rotor wheel, the adaptor member including an adaptor attachment slot that is complementary to the blade attachment member, and an adaptor attachment member that is complementary to the rotor wheel attachment slot. A coverplate is provided, having a coverplate attachment member that is complementary to the rotor wheel attachment slot, and a hook for engaging the adaptor member. When assembled, the coverplate member matingly engages with the adaptor member, and retains the blade in the adaptor member, and the assembly in the rotor wheel.Type: ApplicationFiled: March 31, 2016Publication date: July 21, 2016Applicant: GENERAL ELECTRIC COMPANYInventors: Andres Jose Garcia-Crespo, John McConnell Delvaux, Diane Patricia Miller
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Patent number: 9328622Abstract: An assembly and method for affixing a turbomachine rotor blade to a rotor wheel are disclosed. In an embodiment, an adaptor member is provided disposed between the blade and the rotor wheel, the adaptor member including an adaptor attachment slot that is complementary to the blade attachment member, and an adaptor attachment member that is complementary to the rotor wheel attachment slot. A coverplate is provided, having a coverplate attachment member that is complementary to the rotor wheel attachment slot, and a hook for engaging the adaptor member. When assembled, the coverplate member matingly engages with the adaptor member, and retains the blade in the adaptor member, and the assembly in the rotor wheel.Type: GrantFiled: June 12, 2012Date of Patent: May 3, 2016Assignee: General Electric CompanyInventors: Andres Jose Garcia-Crespo, John McConnell Delvaux, Diane Patricia Miller
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Patent number: 9316109Abstract: A turbine shroud assembly includes an inner shroud portion comprising a body portion having a first circumferential edge, and a discourager extending circumferentially past the first circumferential edge of the body portion, wherein the discourager is integrally formed with the inner shroud portion.Type: GrantFiled: April 10, 2012Date of Patent: April 19, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Thomas Foster, Andres Jose Garcia-Crespo
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Patent number: 9175402Abstract: A turbine repair process, a repaired coating, and a repaired turbine component are disclosed. The turbine repair process includes providing a turbine component having a higher-pressure region and a lower-pressure region, introducing particles into the higher-pressure region, and at least partially repairing an opening between the higher-pressure region and the lower-pressure region with at least one of the particles to form a repaired turbine component. The repaired coating includes a silicon material, a ceramic matrix composite material, and a repaired region having the silicon material deposited on and surrounded by the ceramic matrix composite material. The repaired turbine component a ceramic matrix composite layer and a repaired region having silicon material deposited on and surrounded by the ceramic matrix composite material.Type: GrantFiled: July 30, 2012Date of Patent: November 3, 2015Assignee: General Electric CompanyInventors: Rupak Das, John McConnell Delvaux, Andres Jose Garcia-Crespo