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公开(公告)号：US11125165B2
公开(公告)日：2021-09-21
申请号：US15819443
申请日：2017-11-21
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Adon Delgado, Jr. , Brandon Wayne Miller , Hendrik Pieter Jacobus de Bock
Abstract: 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.
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公开(公告)号：US09676491B2
公开(公告)日：2017-06-13
申请号：US14654685
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Michael Jay Epstein , Adon Delgado, Jr. , Robert Harold Weisgerber
Abstract: 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.
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公开(公告)号：US11815024B2
公开(公告)日：2023-11-14
申请号：US17375489
申请日：2021-07-14
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Adon Delgado, Jr. , Brandon Wayne Miller , Hendrik Pieter Jacobus de Bock
CPC classification number: F02C7/224 , F02C7/14 , F02C7/141 , F28F23/00 , F05D2220/323 , F05D2240/12 , F05D2260/213 , F28F27/02 , F28F2250/06
Abstract: 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.
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公开(公告)号：US10006363B2
公开(公告)日：2018-06-26
申请号：US14655747
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Adon Delgado, Jr. , Todd James Buchholz , Christopher Dale Mathias
CPC classification number: F02C3/22 , B64D37/30 , B64D41/00 , B64D2221/00 , F02C6/08 , F02C7/00 , Y02T50/44 , Y02T50/53 , Y02T90/44
Abstract: 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.
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