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WO2021084389A1 - Moteur à turbine à gaz pourvu d'un récupérateur fendu utilisant un fluide de travail à haute densité - Google Patents

Moteur à turbine à gaz pourvu d'un récupérateur fendu utilisant un fluide de travail à haute densité Download PDF

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Publication number
WO2021084389A1
WO2021084389A1 PCT/IB2020/059940 IB2020059940W WO2021084389A1 WO 2021084389 A1 WO2021084389 A1 WO 2021084389A1 IB 2020059940 W IB2020059940 W IB 2020059940W WO 2021084389 A1 WO2021084389 A1 WO 2021084389A1
Authority
WO
WIPO (PCT)
Prior art keywords
high density
engine
heat exchangers
fluid
pressure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/IB2020/059940
Other languages
English (en)
Inventor
David Lior
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Turbogen Ltd
Original Assignee
Turbogen Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Turbogen Ltd filed Critical Turbogen Ltd
Publication of WO2021084389A1 publication Critical patent/WO2021084389A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
    • F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
    • F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
    • F01K25/103—Carbon dioxide
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
    • F01K7/32—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or overcritical pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/224—Heating fuel before feeding to the burner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit

Definitions

  • the invention relates to recuperated gas turbine engines, and specifically to those having a split recuperator.
  • a recuperator In the design of gas turbines, a recuperator is used to increase thermal efficiency, by recovering energy from the turbine exhaust gas flow.
  • a recuperator In an aero engine, such as a turbofan, turbo prop, or turbo propeller engine, the use of a recuperator is justified if the reduction in thrust specific fuel consumption (TSFC) more than compensates for the added weight of the recuperator.
  • TSFC thrust specific fuel consumption
  • the recuperator In a split recuperator design for a gas turbine engine, the recuperator consists of two (or more) heat exchangers; of which one is located at the turbine outlet and one is located at the last stage compressor outlet or at the combustor inlet.
  • the two heat exchangers are connected by a duct containing a fluid which does not completely evaporate at the maximum turbine outlet temperature.
  • the duct conveys the fluid from the first heat exchanger to the combustor and from the compressor outlet to the second heat exchanger.
  • the duct To reduce pressure losses when the fluid is a gas, the duct must have a large diameter, and this adds considerably to the overall weight of the recuperator and to the overall TSFC in the case of an aero engine.
  • the invention is a lightweight, compact split recuperator in which a high density working fluid, such as supercritical carbon dioxide, flows in a duct joining the two heat exchangers.
  • a high density working fluid such as supercritical carbon dioxide
  • the high density working fluid enables the use of a duct of small diameter and low weight.
  • the flows in the two heat exchangers are controlled by two or more pressure regulators in order to achieve optimal thermal efficiency over a wide range of engine operating conditions, such as those occurring at different flight altitudes and speeds in an aero engine.
  • a gas turbine engine with a split recuperator system which includes at least two heat exchangers connected by one or more ducts through which a high density fluid transfers thermal energy.
  • the high density fluid has a specific heat capacity and a viscosity which vary with pressure over an operational temperature range.
  • At least one of the heat exchangers cools an exhaust fluid from the engine; at least one of the heat exchangers heats a fluid flowing into a combustor of the engine.
  • the thermal efficiency of at least one of the heat exchangers is controlled by a pressure regulator which adjusts a pressure of the high density fluid.
  • the high density fluid is a supercritical liquid, such as supercritical carbon dioxide.
  • the operational temperature range is 500 to 1000 degrees Celsius.
  • the pressure of the high density fluid in the one or more ducts is greater than or equal to 50 bars.
  • the gas turbine engine is a turbofan engine, a turbo shaft engine, or a turbo propeller engine.
  • Fig. 1 A perspective diagram of a turbofan engine with a split recuperator, according to an exemplary embodiment of the invention.
  • Fig. 2 A plot of pressure vs. specific enthalpy for carbon dioxide.
  • Fig. 1 shows a perspective diagram of a turbofan engine 100 with a split recuperator, according to an exemplary embodiment of the invention.
  • Ducts 120 and 220 and heat exchangers 110 and 210 form a closed pressurized tubular system containing a high density fluid, such as supercritical carbon dioxide.
  • the fluid in duct 120 flows from inlet 120 A to outlet 120B, where it enters into hot heat exchanger 110.
  • the fluid in duct 220 flows from inlet 220A to outlet 220B, where it enters into cold heat exchanger 210.
  • the pressure of the high density fluid is controlled by pressure regulators 130 and 230, inserted into ducts 120 and 220, respectively, as shown. Each pressure regulator is controlled by the maximum temperature at its inlet, so as to optimize the thermal efficiencies of heat exchangers 110 and 210. The optimization depends upon the thermodynamic properties of the highly dense fluid, as explained below.
  • Fig. 2 shows a plot of pressure P in units of bars vs. specific enthalpy H in units of kilojoules per kilogram (kJ/kg) for carbon dioxide (CO2).
  • Lines of constant temperature (in units of °C) are shown in red and lines of constant specific volume (in units of cubic meters/kg) are shown in green.
  • CO2 behaves as a high density supercritical liquid, called "SCO2".
  • sCCE as a working fluid derives from the fact that it behaves as a dense liquid even at temperatures over 500 °C, and that its specific volume, viscosity, and specific heat capacity can be controlled by varying its pressure over the operational temperature range, which is, for example, 500 °C to 1000 °C.
  • the units of Cp are kJ/kg/°C.
  • cold heat exchanger 210 heats the air flowing into the combustor of the engine with a thermal efficiency which is proportional to the product of G and Cp.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un moteur à turbine à gaz pourvu d'un système récupérateur fendu qui comprend au moins deux échangeurs de chaleur reliés par un ou plusieurs conduits à travers lesquels un fluide haute densité transfère de l'énergie thermique. La capacité thermique et la viscosité spécifiques du fluide haute densité varient avec la pression sur une plage de température opérationnelle. Au moins l'un des échangeurs de chaleur refroidit un fluide d'échappement provenant du moteur, et au moins l'un des échangeurs de chaleur chauffe un fluide s'écoulant dans une chambre de combustion du moteur. L'efficacité thermique d'au moins l'un des échangeurs de chaleur est régulée par un régulateur de pression.
PCT/IB2020/059940 2019-10-28 2020-10-22 Moteur à turbine à gaz pourvu d'un récupérateur fendu utilisant un fluide de travail à haute densité Ceased WO2021084389A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201962926611P 2019-10-28 2019-10-28
US62/926,611 2019-10-28

Publications (1)

Publication Number Publication Date
WO2021084389A1 true WO2021084389A1 (fr) 2021-05-06

Family

ID=75715800

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2020/059940 Ceased WO2021084389A1 (fr) 2019-10-28 2020-10-22 Moteur à turbine à gaz pourvu d'un récupérateur fendu utilisant un fluide de travail à haute densité

Country Status (1)

Country Link
WO (1) WO2021084389A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140096524A1 (en) * 2009-09-17 2014-04-10 Echogen Power Systems, Llc Heat Engine and Heat to Electricity Systems and Methods with Working Fluid Mass Management Control
US20150033737A1 (en) * 2011-12-02 2015-02-05 Mikhael Mitri Device and method for utilizing the waste heat of an internal combustion engine, in particular for utilizing the waste heat of a vehicle engine
US20170356340A1 (en) * 2016-06-08 2017-12-14 Rolls-Royce Corporation Deep Heat Recovery Gas Turbine Engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140096524A1 (en) * 2009-09-17 2014-04-10 Echogen Power Systems, Llc Heat Engine and Heat to Electricity Systems and Methods with Working Fluid Mass Management Control
US20150033737A1 (en) * 2011-12-02 2015-02-05 Mikhael Mitri Device and method for utilizing the waste heat of an internal combustion engine, in particular for utilizing the waste heat of a vehicle engine
US20170356340A1 (en) * 2016-06-08 2017-12-14 Rolls-Royce Corporation Deep Heat Recovery Gas Turbine Engine

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