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
  • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
• • 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
  • 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
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/78—Other construction of jet pipes
  • F02K1/82—Jet pipe walls, e.g. liners
  • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
• • 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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
  • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
• • 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
  • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
• • 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
• • 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
  • F05D2260/221—Improvement of heat transfer
  • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
  • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

• the present invention relates to heat recovery from the exhaust of a turbomachine.
• the present invention relates to heat recovery with the aim of heating fuel and/or air intended to enter a combustion chamber of said turbomachine.
• the invention applies to any type of exhaust system.
• the turbomachine 2 comprises a fan 4 making it possible to recover air coming from the atmosphere outside the turbomachine 2, a compressor 6, a combustion chamber 8, a turbine 10, and an exhaust system 12.
• a fan 4 making it possible to recover air coming from the atmosphere outside the turbomachine 2, a compressor 6, a combustion chamber 8, a turbine 10, and an exhaust system 12.
• a heat source located nearby is favored so as to increase the thermal efficiency of the turbomachine 2.
• a heat source is for example constituted by the gases leaving through the exhaust system 12, downstream of the turbine 10.
• the positioning of a heat exchanger in the primary exhaust flow 14, for example in the form of fins positioned in the flow induces pressure losses in the turbomachine 2, which negatively impacts the thrust of the aircraft.
• the positioning of a heat exchanger in the turbomachine 2 also harms the compactness of said turbomachine 2.
• the present invention therefore aims to overcome the aforementioned drawbacks and to provide an exhaust system allowing efficient heat recovery at the exhaust of a turbomachine.
• the invention is the result of technological research aimed at very significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft.
• the subject of the present invention is an exhaust system for a turbomachine comprising a nozzle delimiting at least partly a gas exhaust stream, the exhaust system further comprising a heat exchanger comprising at least one distributor, at least one collector and pipes configured to circulate a heat transfer fluid in said pipes between the distributor and the collector, the heat exchanger being configured to carry out thermal exchanges between the gas exhaust stream and the pipes, and the heat exchanger heat being positioned on the nozzle, the pipes being partially formed from a surface of the nozzle.
• a heat exchanger comprising at least one distributor, at least one collector and pipes configured to circulate a heat transfer fluid in said pipes between the distributor and the collector, the heat exchanger being configured to carry out thermal exchanges between the gas exhaust stream and the pipes, and the heat exchanger heat being positioned on the nozzle, the pipes being partially formed from a surface of the nozzle.
• the exhaust system according to the invention allows heat recovery at the level of the exhaust of a turbomachine at the periphery of the exhaust stream without inducing significant pressure losses for the turbomachine, the heat exchanger heat being particularly compact and non-invasive.
• the nozzle comprises an annular external part and a central body, the heat exchanger being positioned on the external part and/or on the central body.
• the external part of the nozzle comprises one or more annular sectors.
• the pipes are positioned outside or inside the gas exhaust stream.
• the pipes have a cross section of semi-circular, or rectangular, or bell-shaped, or semi-elliptical, or triangular shape.
• the pipes extend longitudinally parallel to a longitudinal axis of the exhaust system, or transversely to the longitudinal axis.
• the exhaust system is made of a material comprising a titanium alloy and/or a nickel alloy.
• the heat exchanger is configured to carry out thermal exchanges between exhaust gases leaving through the gas exhaust stream and a heat transfer fluid circulating in the pipes, said heat transfer fluid comprising air and/or water vapor and/or water and/or fuel and/or oil and/or supercritical CO2 and/or liquid or gaseous hydrogen.
• the present invention also relates to a turbomachine comprising a compressor, a combustion chamber and an exhaust system as defined previously, the heat exchanger being configured to heat fuel at the inlet of the combustion chamber and/or the air leaving the compressor before entering the combustion chamber.
• the present invention also relates to an aircraft comprising a turbomachine as defined above and/or an exhaust system as defined above.
• the present invention further relates to the use of the exhaust system as defined above in a thermal management system for heating air or fuel in a turbomachine.
• FIG 1 is a longitudinal and schematic sectional view of a turbomachine of an aircraft according to the state of the art
• FIG 2 is a schematic longitudinal sectional view of a turbomachine of an aircraft according to the invention
• FIG 3 is a schematic view of a first embodiment of an exhaust system for a turbomachine according to the invention.
• FIG 4 is a schematic view of a first variant of the first embodiment of an exhaust system for a turbomachine illustrated in Figure 3;
• FIG 5 is a schematic view of a second variant of the first embodiment of an exhaust system for a turbomachine illustrated in Figure 3;
• FIG 6 is a schematic view of a third variant of the first embodiment of an exhaust system for a turbomachine illustrated in Figure 3;
• FIG 7 is a schematic view of a second embodiment of an exhaust system for a turbomachine according to the invention.
• FIG 8 is a schematic view of the first embodiment of an exhaust system of Figure 3 comprising an outer skin
• FIG 9 is a schematic sectional view of pipes whose cross section is semi-circular.
• FIG 10 is a schematic sectional view of pipes whose cross section is triangular.
• a turbomachine 16 of an aircraft according to the invention is shown schematically in Figure 2.
• the turbomachine 16 comprises a fan 4 making it possible to recover air coming from the atmosphere outside the turbomachine 16, a compressor 6, a combustion chamber 8, a turbine 10, and an exhaust system 18.
• the exhaust system 12 comprises a nozzle 20 preferably comprising an annular external part 21 and a central body 22 forming an exhaust stream 24 of exhaust gas. annular section.
• the exhaust system 18 also includes a heat exchanger 26 configured to heat fuel entering the combustion chamber 8 and/or air leaving the compressor 6 and before entering the combustion chamber 8.
• FIG 3 shows schematically a first embodiment of an exhaust system 18 in which the heat exchanger 26 is positioned on the external part 21 of the nozzle 20, the central body 22 not being shown in Figure 3 as well as in the following figures.
• the heat exchanger 26 can be positioned on the central body 22 of the exhaust system 18.
• the heat exchanger 26 comprises at least one distributor 28, at least one collector 30 and pipes 32.
• the distributor 28 is configured to inject a heat transfer fluid into the pipes 32 themselves configured to circulate said heat transfer fluid in said pipes 32 to a collector 30 configured to recover the heated heat transfer fluid.
• the heat transfer fluid comprises for example air, and/or water vapor, and/or water, and/or fuel, and/or oil, and/or supercritical CO2 and /or liquid hydrogen, and/or fuel for supplying the turbomachine 16.
• Liquid hydrogen can for example be used as fuel and is advantageously used as a heat transfer fluid since it is a fuel cold, its boiling temperature being around 20 Kelvin.
• the pipes 32 are partially formed from a surface 34 of the external part 21 of the nozzle 20 or from a surface of the central body if necessary.
• the surface is a surface of the nozzle wall, also called the primary exhaust wall, upon contact with which the exhaust gases are expelled.
• the pipes 32, as well as the distributors 28 and collectors 30 are positioned in a preferred manner on the exterior surface 34 of the wall of the external part 21 of the nozzle 20, in other words outside the exhaust stream 24 in order to do not disrupt the flow exhaust.
• the pipes 32 can nevertheless be positioned on the interior surface of the wall of the nozzle 20, in other words inside the exhaust vein 24.
• the pipes 32 are distributed over the entire periphery of the vein exhaust 24.
• the heat exchanger 26 is configured to carry out thermal exchanges between the gas exhaust stream 24 and the pipes 32 via the and/or the walls of the nozzle 20.
• the exhaust system 18 as shown in Figure 3 comprises four annular sectors 36 of substantially the same dimensions, at least one collector 30, at least one distributor 28 and pipes 32 being positioned on each sector 36, the collector 30 and distributor 28 adjoining two different sectors 36 being connected by a tube 38.
• the exhaust system 18 comprises a single annular sector or several annular sectors.
• the pipes 32 extend along the periphery of the external part 21 of the nozzle 20, transversely to the longitudinal axis L of the exhaust system 18.
• the heat exchanger 26 comprises non-bent pipes 32, the only curvature of which is the curvature of the external part 21 of the nozzle 20.
• a first variant of the first embodiment is shown schematically in Figure 4.
• the pipes 32 extend along the periphery of the external part 21 of the nozzle 20 in a winding manner.
• the pipes 32 have bends 40 of angle substantially equal to 180° so that each collector 30 and distributor 28 includes few inlets and outlets towards pipes 32, in order to minimize the flow of fluid passing through the pipes 32. exchanger.
• a second variant of the first embodiment is shown schematically in Figure 5.
• This variant is identical to the embodiment of Figure 3, except that the pipes 32 extend longitudinally and substantially parallel to the longitudinal axis L of the exhaust system 18.
• a third variant of the first embodiment is shown schematically in Figure 6.
• This variant is identical to the embodiment of Figure 4, except that the pipes 32 extend longitudinally and substantially parallel to the longitudinal axis L of the exhaust system 18.
• the pipes 32 also have angle bends 40 substantially equal to 180°.
• FIG. 7 shows schematically a second embodiment of an exhaust system 18 in which the heat exchanger 26 is positioned on the external part 21 of the nozzle 20.
• the pipes 32 are positioned inside the exhaust vein 24 while the distributors 28 and collectors 30 are positioned outside the exhaust vein 24.
• the pipes 32 extend substantially parallel to the longitudinal axis L of the exhaust system 18.
• This embodiment makes it possible to increase the heat exchange surface, at the expense of a slight pressure loss in the primary flow of the turbomachine.
• the exhaust system 18 is made of a thermally resistant material, for example a material comprising a titanium alloy and/or a nickel alloy.
• the exhaust system 18 can optionally comprise an outer skin 42, as illustrated in FIG. 8, arranged annularly around the heat exchanger 18 and serving as an aerodynamic fairing of the flow of the secondary vein or any other flow coming from the turbomachine.
• the exhaust system can also include a flange 44 at the longitudinal end of the nozzle 20 so as to attach said nozzle 20 to the turbomachine 2.
• the pipes 32 have for example a cross section of semi-circular, or rectangular, or bell-shaped, or semi-elliptical, or even triangular shape.
• the shape of the section of the pipes 32 also allows the pipes to be easily dismantled during their manufacture.
• Figure 9 shows schematically a sectional view of pipes 32 whose cross section is semi-circular.
• the sectional view is here taken along the longitudinal axis of the exhaust system 18.
• the pipes 32 shown are for example the pipes 32 presented in the embodiment of Figure 3. They are protected by the outer skin 42.
• Figure 10 shows a sectional view of pipes 32 whose cross section is triangular.
• the sectional view is taken transversely to the longitudinal axis L of the exhaust system 18.
• the pipes 32 shown are for example the pipes 32 presented in the embodiment of Figure 7, in which the pipes 32 are positioned in the exhaust vein 24 and extend parallel to the longitudinal axis L of the exhaust system.
• the triangular section of the pipes 32 allows a large heat exchange surface and a low pressure loss.
• one of the sides of each pipe 32 is advantageously oriented radially in the direction of the longitudinal axis L, thus allowing easier demolding during the manufacture of the exhaust system 18.
• manufacturing is preferably carried out by diffusion welding of a stack of several sheets, an inert gas being injected at the desired location of the pipes 32.
• Diffusion welding makes it possible to avoid a reduction at the welds, and thus makes it possible to produce an exhaust system 18 having substantially the same properties as if the latter were made in a single piece.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=85278388

Family Applications (1)

Country Status (5)

Family Cites Families (4)

• 2022
  • 2022-08-02 FR FR2208020A patent/FR3138671B1/fr active Active
• 2023
  • 2023-07-28 WO PCT/FR2023/051203 patent/WO2024028551A1/fr not_active Ceased
  • 2023-07-28 CN CN202380057269.0A patent/CN119630869A/zh active Pending
  • 2023-07-28 EP EP23761173.6A patent/EP4565778A1/de active Pending
  • 2023-07-28 US US19/099,468 patent/US20260055730A1/en active Pending

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