Patents by Inventor Raymond Floyd Martell
Raymond Floyd Martell 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: 11905842Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.Type: GrantFiled: December 16, 2021Date of Patent: February 20, 2024Assignee: General Electric CompanyInventors: Ashish Sharma, Tomasz Edward Berdowski, Maciej CzerwiĆski, Katarzyna Anna Mikolajczyk, Raymond Floyd Martell, Tomasz Jan Bulsiewicz
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Publication number: 20230258407Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.Type: ApplicationFiled: April 19, 2023Publication date: August 17, 2023Applicant: General Electric CompanyInventors: Ramon Martinez, Raymond Floyd Martell, Donald Lee Gardner
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Patent number: 11719115Abstract: A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.Type: GrantFiled: December 23, 2021Date of Patent: August 8, 2023Assignees: GENERAL ELECTRIC COMPANY, GENERAL ELECTRIC DEUTSCHLAND HOLDING GMBH, GENERAL ELECTRIC COMPANY POLSKA SP. Z O.OInventors: Tomasz Edward Berdowski, Ashish Sharma, Raymond Floyd Martell, Piotr Jerzy Kulinski, Lukasz Maciej Janczak
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Publication number: 20230193784Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.Type: ApplicationFiled: December 16, 2021Publication date: June 22, 2023Inventors: Ashish Sharma, Tomasz Edward Berdowski, Maciej Czerwinski, Katarzyna Anna Mikolajczyk, Raymond Floyd Martell, Tomasz Jan Bulsiewicz
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Patent number: 11662150Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.Type: GrantFiled: August 13, 2020Date of Patent: May 30, 2023Assignee: General Electric CompanyInventors: Ramon Martinez, Raymond Floyd Martell, Donald Lee Gardner
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Publication number: 20230147089Abstract: A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.Type: ApplicationFiled: December 23, 2021Publication date: May 11, 2023Inventors: Tomasz Edward Berdowski, Ashish Sharma, Raymond Floyd Martell, Piotr Jerzy Kulinski, Lukasz Maciej Janczak
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Publication number: 20220049904Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.Type: ApplicationFiled: August 13, 2020Publication date: February 17, 2022Inventors: Ramon Martinez, Raymond Floyd Martell, Donald Lee Gardner
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Patent number: 11118535Abstract: A thrust balancing gear assembly for a turbo machine is provided. The gear assembly includes an input gear connected to an input drive shaft, an output gear connected to an output drive shaft, and a compound planet gear including a first planet gear and a second planet gear each connected to one another and positioned in axially adjacent arrangement. The first planet gear is connected to the input gear at a first interface and the second planet gear is connected to the output gear at a second interface.Type: GrantFiled: March 5, 2019Date of Patent: September 14, 2021Assignee: General Electric CompanyInventors: Gert Johannes van der Merwe, Raymond Floyd Martell
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Patent number: 11092084Abstract: A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.Type: GrantFiled: May 26, 2016Date of Patent: August 17, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Kwanwoo Kim, Raymond Floyd Martell, Alfred Albert Mancini, Clayton S. Cooper
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Patent number: 11022037Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.Type: GrantFiled: January 4, 2018Date of Patent: June 1, 2021Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Brandon Wayne Miller, Raymond Floyd Martell, Jeffrey Douglas Rambo, Ryan James Matthys, Joel Francis Kirk
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Patent number: 10940535Abstract: A binder jet printed article includes a part having a top portion, a bottom portion, and an overhang extending from the top portion and a support structure formed around the part that may block deformation of the part during post-printing thermal processing. The support structure includes a skid positioned adjacent to the bottom portion that may support the part, a first plurality of support features disposed along an outer perimeter of the skid, and a second plurality of support features disposed on the top portion of the printed part. The first and second plurality of support features form a lattice around the printed part such that the printed part is nested within the support structure.Type: GrantFiled: June 8, 2018Date of Patent: March 9, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Ananda Barua, Sathyanarayanan Raghavan, Ken Salas Nobrega, Arunkumar Natarajan, Vadim Bromberg, Raymond Floyd Martell, Meghan J. Borz
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Patent number: 10781721Abstract: Turbine center frames are provided. For example, a turbine center frame comprises an annular outer case and an annular hub. The hub is defined radially inward of the outer case such that the outer case circumferentially surrounds the hub. The turbine center frame further comprises an annular fairing extending between the outer case and the hub, a ligament extending from the fairing to the outer case to connect the fairing to the outer case, a plurality of struts extending from the hub to the outer case, and a boss structure defined on an outer surface of the outer case. The outer case, hub, fairing, ligament, plurality of struts, and boss structure are integrally formed as a single monolithic component. For instance, the turbine center frame is additively manufactured as an integral structure, and methods for manufacturing turbine center frames also are provided.Type: GrantFiled: February 9, 2018Date of Patent: September 22, 2020Assignee: General Electric CompanyInventors: Ananda Barua, Joshua Tyler Mook, Raymond Floyd Martell, Changjie Sun, Gautam Naik, Jordan Paule Tesorero, Aigbedion Akwara
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Publication number: 20200284223Abstract: A thrust balancing gear assembly for a turbo machine is provided. The gear assembly includes an input gear connected to an input drive shaft, an output gear connected to an output drive shaft, and a compound planet gear including a first planet gear and a second planet gear each connected to one another and positioned in axially adjacent arrangement. The first planet gear is connected to the input gear at a first interface and the second planet gear is connected to the output gear at a second interface.Type: ApplicationFiled: March 5, 2019Publication date: September 10, 2020Inventors: Gert Johannes van der Merwe, Raymond Floyd Martell
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Patent number: 10753455Abstract: A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.Type: GrantFiled: February 7, 2019Date of Patent: August 25, 2020Assignee: General Electric CompanyInventors: Gert Johannes van der Merwe, Raymond Floyd Martell
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Patent number: 10711693Abstract: A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.Type: GrantFiled: July 12, 2017Date of Patent: July 14, 2020Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Raymond Floyd Martell, Mark Leonard Hopper, Scott Douglas Waun
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Publication number: 20190375008Abstract: A binder jet printed article includes a part having a top portion, a bottom portion, and an overhang extending from the top portion and a support structure formed around the part that may block deformation of the part during post-printing thermal processing. The support structure includes a skid positioned adjacent to the bottom portion that may support the part, a first plurality of support features disposed along an outer perimeter of the skid, and a second plurality of support features disposed on the top portion of the printed part. The first and second plurality of support features form a lattice around the printed part such that the printed part is nested within the support structure.Type: ApplicationFiled: June 8, 2018Publication date: December 12, 2019Inventors: Ananda Barua, Sathyanarayanan Raghavan, Ken Salas Nobrega, Arunkumar Natarajan, Vadim Bromberg, Raymond Floyd Martell, Meghan J. Borz
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Publication number: 20190249570Abstract: Turbine center frames are provided. For example, a turbine center frame comprises an annular outer case and an annular hub. The hub is defined radially inward of the outer case such that the outer case circumferentially surrounds the hub. The turbine center frame further comprises an annular fairing extending between the outer case and the hub, a ligament extending from the fairing to the outer case to connect the fairing to the outer case, a plurality of struts extending from the hub to the outer case, and a boss structure defined on an outer surface of the outer case. The outer case, hub, fairing, ligament, plurality of struts, and boss structure are integrally formed as a single monolithic component. For instance, the turbine center frame is additively manufactured as an integral structure, and methods for manufacturing turbine center frames also are provided.Type: ApplicationFiled: February 9, 2018Publication date: August 15, 2019Inventors: Ananda Barua, Joshua Tyler Mook, Raymond Floyd Martell, Changjie Sun, Gautam Naik, Jordan Paule Tesorero, Aigbedion Akwara
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Publication number: 20190203644Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.Type: ApplicationFiled: January 4, 2018Publication date: July 4, 2019Inventors: Daniel Alan Niergarth, Brandon Wayne Miller, Raymond Floyd Martell, Jeffrey Douglas Rambo, Ryan James Matthys, Joel Francis Kirk
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Publication number: 20190170239Abstract: A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.Type: ApplicationFiled: February 7, 2019Publication date: June 6, 2019Inventors: Gert Johannes van der Merwe, Raymond Floyd Martell
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Patent number: 10247296Abstract: A gearbox and a method for additively manufacturing the gearbox are provided. The gearbox includes a housing having an integral heat exchanger additively manufactured within the housing. The heat exchanger includes a plurality of heat exchange passageways for transferring heat between two or more fluids. The heat exchanger is defined at any suitable location or locations within the housing, for example, within voids defined between the walls of the housing and components housed within housing, such as driveshafts, gears, bearings, etc.Type: GrantFiled: December 12, 2016Date of Patent: April 2, 2019Assignee: General Electric CompanyInventors: Gert Johannes van der Merwe, Raymond Floyd Martell