Patents by Inventor Lana Maria Osusky
Lana Maria Osusky 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: 11840941Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation: ( D H + 2 ? t ) 2 ( ( D H + 2 ? t ) / D H ) 1 / 3 to define a performance area factor (PAF).Type: GrantFiled: February 16, 2022Date of Patent: December 12, 2023Assignee: General Electric CompanyInventors: Lana Maria Osusky, Gustavo A. Ledezma, Daniel Endecott Osgood, Gregory Alexander Natsui
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Publication number: 20230349329Abstract: A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 298.17 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m2/m3 and 13,000 m2/m3.Type: ApplicationFiled: May 10, 2023Publication date: November 2, 2023Inventors: Eyitayo James Owoeye, Lana Maria Osusky, Bugra Han Ertas
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Publication number: 20230340888Abstract: An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.Type: ApplicationFiled: June 27, 2023Publication date: October 26, 2023Inventors: Constantinos Minas, Harry Kirk Mathews, JR., Gregory Alexander Natsui, Lana Maria Osusky
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Publication number: 20230323815Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising 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; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.Type: ApplicationFiled: April 11, 2022Publication date: October 12, 2023Inventors: Gregory Alexander Natsui, Giridhar Jothiprasad, Lana Maria Osusky, Thomas Malkus
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Publication number: 20230323813Abstract: An heat exchanger and method for forming the heat exchanger, the heat exchanger including a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter, wherein an average fluid temperature (Tf) to material temperature limit (Tm) ratio (Tf/Tm) is greater than 0 and less than or equal to 1.25 (0<Tf/Tm?1.25), and wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation: T f T m ยท D H 2 / 3 ( D H + t ) ( D H + 2 ? t ) 8 / 3 to define a unit cell performance factor (UCPF).Type: ApplicationFiled: April 8, 2022Publication date: October 12, 2023Inventors: Lana Maria Osusky, Daniel Endecott Osgood
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Publication number: 20230258091Abstract: An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (DH) relate to each other by an equation: ( D H + 2 ? t ) 2 ( ( D H + 2 ? t ) / D H ) 1 / 3 to define a performance area factor (PAF).Type: ApplicationFiled: February 16, 2022Publication date: August 17, 2023Inventors: Lana Maria Osusky, Gustavo A. Ledezma, Daniel Endecott Osgood, Gregory Alexander Natsui
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Patent number: 11702952Abstract: An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.Type: GrantFiled: November 11, 2021Date of Patent: July 18, 2023Assignee: General Electric CompanyInventors: Constantinos Minas, Harry Kirk Mathews, Jr., Gregory Alexander Natsui, Lana Maria Osusky
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Patent number: 11680530Abstract: A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 48 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m2/m3 and 13,000 m2/m3.Type: GrantFiled: April 27, 2022Date of Patent: June 20, 2023Assignee: General Electric CompanyInventors: Eyitayo James Owoeye, Lana Maria Osusky, Bugra Han Ertas
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Publication number: 20230141059Abstract: An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.Type: ApplicationFiled: November 11, 2021Publication date: May 11, 2023Inventors: Constantinos Minas, Harry Kirk Mathews, JR., Gregory Alexander Natsui, Lana Maria Osusky
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Patent number: 11387699Abstract: A generator, which may be used in a wind turbine, has a first stationary component carrying a first winding configuration and a second rotating component carrying a second winding configuration. The second rotating component includes a body portion and a plurality of teeth spaced around and extending radially from the body portion. The second winding configuration is arranged in slots defined between adjacent teeth. A housing is arranged around and rotates with the body portion. A heat exchange circuit is arranged on the second rotating component and includes a coolant channel defined in the teeth; a pump; and a heat exchanger arranged on the housing so as to rotate with the housing, the heat exchanger transverse to a rotational direction of the housing.Type: GrantFiled: December 15, 2020Date of Patent: July 12, 2022Assignee: General Electric Renovables Espana, S.L.Inventors: Roelof Willem Schuring, Lana Maria Osusky, Andrew Thomas Cross, David Allan Torrey
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Publication number: 20220190663Abstract: A generator, which may be used in a wind turbine, has a first stationary component carrying a first winding configuration and a second rotating component carrying a second winding configuration. The second rotating component includes a body portion and a plurality of teeth spaced around and extending radially from the body portion. The second winding configuration is arranged in slots defined between adjacent teeth. A housing is arranged around and rotates with the body portion. A heat exchange circuit is arranged on the second rotating component and includes a coolant channel defined in the teeth; a pump; and a heat exchanger arranged on the housing so as to rotate with the housing, the heat exchanger transverse to a rotational direction of the housing.Type: ApplicationFiled: December 15, 2020Publication date: June 16, 2022Inventors: Roelof Willem Schuring, Lana Maria Osusky, Andrew Thomas Cross, David Allan Torrey
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Patent number: 11098596Abstract: A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.Type: GrantFiled: June 15, 2017Date of Patent: August 24, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Zachary John Snider, Daniel Burnos, Lana Maria Osusky, Brian Gene Brzek, Gregory Thomas Foster
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Patent number: 10227877Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the pressure and suction side cavities; and a second leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the second leading edge cavity located forward of the first leading edge cavity.Type: GrantFiled: August 18, 2016Date of Patent: March 12, 2019Assignee: General Electric CompanyInventors: David Wayne Weber, Lana Maria Osusky
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Patent number: 10221696Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.Type: GrantFiled: August 18, 2016Date of Patent: March 5, 2019Assignee: General Electric CompanyInventors: David Wayne Weber, Lana Maria Osusky
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Patent number: 10208608Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.Type: GrantFiled: August 18, 2016Date of Patent: February 19, 2019Assignee: General Electric CompanyInventors: David Wayne Weber, Gregory Thomas Foster, Michelle Jessica Iduate, Lana Maria Osusky
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Patent number: 10208607Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.Type: GrantFiled: August 18, 2016Date of Patent: February 19, 2019Assignee: General Electric CompanyInventors: David Wayne Weber, Gregory Thomas Foster, Lana Maria Osusky
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Publication number: 20180363470Abstract: A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.Type: ApplicationFiled: June 15, 2017Publication date: December 20, 2018Inventors: Zachary John Snider, Daniel Burnos, Lana Maria Osusky, Brian Gene Brzek, Gregory Thomas Foster
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Publication number: 20180051573Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.Type: ApplicationFiled: August 18, 2016Publication date: February 22, 2018Inventors: David Wayne Weber, Lana Maria Osusky
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Publication number: 20180051574Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.Type: ApplicationFiled: August 18, 2016Publication date: February 22, 2018Inventors: David Wayne Weber, Gregory Thomas Foster, Lana Maria Osusky
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Publication number: 20180051576Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the pressure and suction side cavities; and a second leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the second leading edge cavity located forward of the first leading edge cavity.Type: ApplicationFiled: August 18, 2016Publication date: February 22, 2018Inventors: David Wayne Weber, Lana Maria Osusky