Patents by Inventor Adon Delgado
Adon Delgado 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: 20240039077Abstract: Energy storage radiators are disclosed. The structure of the radiator may be used as a battery to store and release energy, as well as serving to regulate the temperature of that battery and the associated device or vehicle. The structure may be configured to provide mechanical support, an enclosure, an attachment point, or an extension for a vehicle or a device. By designing an energy storage radiator to function as a battery, a separate battery superstructure may not be required. Also, the heat to be radiated away can be used to keep the battery in its operating temperature range. This may provide mass reduction of the radiator structures or materials, as well as make those materials multifunctional and replace material elsewhere with respect to conventional systems.Type: ApplicationFiled: July 28, 2022Publication date: February 1, 2024Applicant: The Aerospace CorporationInventors: Eric Joseph NEMANICK, Henry HELVAJIAN, Adon DELGADO, JR., Kristine L. FERRONE
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Publication number: 20240021336Abstract: Scalable radioisotope power tiles that can provide heat, electrical power, or both, are disclosed. Unlike conventional radioisotope thermoelectric generator (RTG) designs, the scalable radioisotope power tiles do not necessarily seek to minimize the RTG surface area. Rather, a planar design may be used to maximize the radiative surface to increase the temperature difference (?T) and increase system heat to electricity conversion efficiency where electrical power generation is desired. In addition, such a planar design can be one-sided or two-sided, allowing for flexibility in design. For instance, such power tiles may be deployed in a material like a solar sail, on the surface of a vehicle, in terrestrial systems, etc.Type: ApplicationFiled: July 14, 2022Publication date: January 18, 2024Applicant: The Aerospace CorporationInventors: Eric Joseph NEMANICK, Henry HELVAJIAN, Adon DELGADO, JR., Kristine L. FERRONE
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Patent number: 11815024Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.Type: GrantFiled: July 14, 2021Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Adon Delgado, Jr., Brandon Wayne Miller, Hendrik Pieter Jacobus de Bock
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Publication number: 20210340914Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.Type: ApplicationFiled: July 14, 2021Publication date: November 4, 2021Inventors: Daniel Alan Niergarth, Adon Delgado, JR., Brandon Wayne Miller, Hendrik Pieter Jacobus de Bock
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Patent number: 11125165Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.Type: GrantFiled: November 21, 2017Date of Patent: September 21, 2021Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Adon Delgado, Jr., Brandon Wayne Miller, Hendrik Pieter Jacobus de Bock
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Publication number: 20190153953Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.Type: ApplicationFiled: November 21, 2017Publication date: May 23, 2019Inventors: Daniel Alan Niergarth, Adon Delgado, JR., Brandon Wayne Miller, Hendrik Pieter Jacobus de Bock
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Patent number: 10006363Abstract: An electrical power system for an aircraft including a turbine engine coupled to the aircraft and providing propulsive thrust and emitting heat during operation to define a high temperature source, a cryogenic fuel system located within the aircraft and providing fuel for the turbine and emitting heat at a lower temperature than the heat from the turbine engine to define a low temperature source and an electrical power generator located on the aircraft and having a thermodynamic generator using the temperature difference to generate electrical power and a method for producing electric power.Type: GrantFiled: November 26, 2013Date of Patent: June 26, 2018Assignee: General Electric CompanyInventors: Adon Delgado, Jr., Todd James Buchholz, Christopher Dale Mathias
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Patent number: 9765691Abstract: A turbine engine assembly including a turbine core and a cryogenic fuel system. The turbine core includes: a compressor section; a combustion section; and a turbine section, which are axially aligned. The a cryogenic fuel system includes: a cryogenic fuel reservoir; a vaporizer heat exchanger; a liquid supply line operably coupling the fuel reservoir to an input of the vaporizer heat exchanger; a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section; and a second heat exchanger thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line.Type: GrantFiled: November 26, 2013Date of Patent: September 19, 2017Assignee: General Electric CompanyInventors: Adon Delgado, Todd James Buchholz, Christopher Dale Mathias
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Patent number: 9676491Abstract: A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter fluidly coupled to the pressure vent.Type: GrantFiled: November 26, 2013Date of Patent: June 13, 2017Assignee: General Electric CompanyInventors: Michael Jay Epstein, Adon Delgado, Jr., Robert Harold Weisgerber
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Publication number: 20160025339Abstract: A method and apparatus of using cryogenic fuel in an engine for an aircraft wherein the cryogenic fuel is supplied to the engine for combustion.Type: ApplicationFiled: March 12, 2014Publication date: January 28, 2016Inventors: Deepak Manohar KAMATH, Adon DELGADO, JR., Michael Jay EPSTEIN
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Publication number: 20150344143Abstract: A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter fluidly coupled to the pressure vent.Type: ApplicationFiled: November 26, 2013Publication date: December 3, 2015Applicant: General Electric CompanyInventors: Michael Jay EPSTEIN, Adon DELGADO, Jr., Robert Harold WEISGERBER
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Publication number: 20150337730Abstract: Turbine engine assemblies including a turbine engine assembly having a turbine core comprising a compressor section, a combustion section, a turbine section, and a nozzle section, which are axially aligned, wherein the combustion section comprises a generally annular case having inner and outer walls, a heat exchanger comprising multiple passages in proximity to at least one of the inner and outer walls, with the passages arranged about at least a portion of the case and in fluid communication with each other such that fluid may flow through the passages and a cryogenic fuel system having a cryogenic fuel tank with a supply line coupled to one of the passages, wherein cryogenic fuel may be supplied from the cryogenic fuel tank, through the supply line, to the passages of the heat exchanger, where the fuel in the passages may be heated by the combustion section. The heat exchanger may be a single or multistage vaporizer.Type: ApplicationFiled: November 26, 2013Publication date: November 26, 2015Inventors: Thomas KUPISZEWSKI, Michael Jay EPSTEIN, Todd James BUCHHOLZ, Adon DELGADO, Christopher Dale MATHIAS, Deborah Ann OAKES
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Publication number: 20150330312Abstract: A turbine engine assembly including a turbine core and a cryogenic fuel system. The turbine core includes: a compressor section; a combustion section; and a turbine section, which are axially aligned. The a cryogenic fuel system includes: a cryogenic fuel reservoir; a vaporizer heat exchanger; a liquid supply line operably coupling the fuel reservoir to an input of the vaporizer heat exchanger; a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section; and a second heat exchanger thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line.Type: ApplicationFiled: November 26, 2013Publication date: November 19, 2015Inventors: Adon DELGADO, Todd James BUCHHOLZ, Christopher Dale MATHIAS
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Publication number: 20150330303Abstract: An electrical power system for an aircraft including a turbine engine coupled to the aircraft and providing propulsive thrust and emitting heat during operation to define a high temperature source, a cryogenic fuel system located within the aircraft and providing fuel for the turbine and emitting heat at a lower temperature than the heat from the turbine engine to define a low temperature source and an electrical power generator located on the aircraft and having a thermodynamic generator using the temperature difference to generate electrical power and a method for producing electric power.Type: ApplicationFiled: November 26, 2013Publication date: November 19, 2015Inventors: Adon DELGADO, JR., Todd James BUCHHOLZ, Christopher Dale MATHIAS
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Publication number: 20130291857Abstract: The disclosed solar power system includes an oil circuit, a molten salt circuit, and a heat exchanger in communication with both the oil and molten salt circuits. The disclosed heat exchanger includes at least one heat pipe, the ends of which are within first and second plenums provided by spaced-apart housings.Type: ApplicationFiled: May 1, 2012Publication date: November 7, 2013Inventors: Robert Zachary Litwin, Adon Delgado, JR.
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Lightweight protector against micrometeoroids and orbital debris (MMOD) impact using foam substances
Patent number: 7465500Abstract: Methods and apparatus are provided for a shield to protect a surface from the impact of hyper-velocity projectiles. The apparatus comprises a foam material that is configured to cover the surface to be protected and is attached directly to that surface. A coating material is typically disposed on the outer surface of the foam material and may penetrate the foam material to a predetermined depth. The foam material and the coating material are selected to form a composite having predetermined values of sonic velocity, toughness, and thermal conductivity. The composite of foam material and coating material can be significantly lighter in weight than a metal shield having equivalent protective characteristics.Type: GrantFiled: October 28, 2004Date of Patent: December 16, 2008Assignee: The Boeing CompanyInventors: Sherwin Yang, Nathan J. Hoffman, Adon Delgado, Jr., Alan V. Von Arx, Michael P. Moriarty, Kathleen M. Sevener, Gerard D. Pelletier -
Patent number: 7143813Abstract: Methods and apparatus are provided for a lightweight heat rejection system suitable for spacecraft applications. The apparatus comprises a manifold configured with an array of heat pipes in thermal contact with a manifold coolant. The heat pipes transfer the coolant heat to associated bumper/radiators external to the manifold. The bumper/radiators are fabricated from a lightweight thermally conductive foam material. The bumper portion protects the heat pipe from space debris and the radiator portion dissipates the heat transferred from the heat pipe through the bumper to the radiator portion. The foam bumper/radiator can be cast over the heat pipe in a relatively simple and economical manufacturing process.Type: GrantFiled: July 28, 2004Date of Patent: December 5, 2006Assignee: The Boeing CompanyInventors: Adon Delgado, Jr., Michael P. Moriarty, Alan von Arx
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Patent number: 7106777Abstract: A phase-change heat exchanger is provided for thermally conditioning a fluid. The phase-change heat exchanger includes, but is not limited to, conduits configured to convey the fluid through the phase-change heat exchanger and a foam structure in thermal contact with at least one of the conduits. The foam structure has ligaments interconnected to form a three-dimensional reticulated structure of open cells. A phase-change material is contained within the open cells and the phase-change material is configured to receive thermal energy of the fluid from the ligaments of the foam structure.Type: GrantFiled: December 8, 2003Date of Patent: September 12, 2006Assignee: The Boeing CompanyInventors: Adon Delgado, Jr., Randall Gene Leonard, Alan Zachary Ullman
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Lightweight protector against micrometeoroids and orbital debris (MMOD) impact using foam substances
Publication number: 20060090636Abstract: Methods and apparatus are provided for a shield to protect a surface from the impact of hyper-velocity projectiles. The apparatus comprises a foam material that is configured to cover the surface to be protected and is attached directly to that surface. A coating material is typically disposed on the outer surface of the foam material and may penetrate the foam material to a predetermined depth. The foam material and the coating material are selected to form a composite having predetermined values of sonic velocity, toughness, and thermal conductivity. The composite of foam material and coating material can be significantly lighter in weight than a metal shield having equivalent protective characteristics.Type: ApplicationFiled: October 28, 2004Publication date: May 4, 2006Inventors: Sherwin Yang, Nathan Hoffman, Adon Delgado, Alan Von Arx, Michael Moriarty, Kathleen Sevener, Gerard Pelletier -
Publication number: 20060021738Abstract: Methods and apparatus are provided for a lightweight heat rejection system suitable for spacecraft applications. The apparatus comprises a manifold configured with an array of heat pipes in thermal contact with a manifold coolant. The heat pipes transfer the coolant heat to associated bumper/radiators external to the manifold. The bumper/radiators are fabricated from a lightweight thermally conductive foam material. The bumper portion protects the heat pipe from space debris and the radiator portion dissipates the heat transferred from the heat pipe through the bumper to the radiator portion. The foam bumper/radiator can be cast over the heat pipe in a relatively simple and economical manufacturing process.Type: ApplicationFiled: July 28, 2004Publication date: February 2, 2006Inventors: Adon Delgado, Michael Moriarty, Alan von Arx