EP3213025B1 - Echangeur de chaleur et turbomoteur comportant un tel echangeur - Google Patents

Echangeur de chaleur et turbomoteur comportant un tel echangeur Download PDF

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Publication number
EP3213025B1
EP3213025B1 EP15790610.8A EP15790610A EP3213025B1 EP 3213025 B1 EP3213025 B1 EP 3213025B1 EP 15790610 A EP15790610 A EP 15790610A EP 3213025 B1 EP3213025 B1 EP 3213025B1
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EP
European Patent Office
Prior art keywords
membrane
fluid
heat exchanger
blade
heat
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.)
Active
Application number
EP15790610.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3213025A1 (fr
Inventor
Gilles Yves AOUIZERATE
Benjamin BOUDSOCQ
Gérard Philippe Gauthier
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.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3213025A1 publication Critical patent/EP3213025A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F27/00—Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
    • F28D2021/0021—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for aircrafts or cosmonautics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2215/00—Fins
    • F28F2215/14—Fins in the form of movable or loose fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2255/00—Heat exchanger elements made of materials having special features or resulting from particular manufacturing processes
    • F28F2255/02—Flexible elements

Definitions

  • the present invention relates to the field of heat exchangers and their application to the cooling of fluids of a turbine engine, such as a turbojet engine or turboprop engine, the exchanger being disposed in particular on a wall of the turbine engine or the nacelle thereof. this.
  • the applicant has set a goal to reduce the pressure drop that the heat exchanger is likely to create on the secondary air flow when the need for cooling is lower. More generally, the applicant has set himself the goal of producing a heat exchanger whose heat exchange between the moving fluids can be controlled so as to reduce the impact of the exchanger parts on the flow characteristics of the heat exchanger. one of the fluids when desired.
  • a heat exchanger between a first fluid and a second fluid comprising a membrane separating the two fluids and a heat conducting element in thermal contact with the membrane on the one hand and the first fluid on the other.
  • said heat conducting element being movable between an active position and an inactive position, such that the heat exchange capacity with the first fluid is lower in the inactive position than in the active position, characterized in that said element is prestressed in the active position and the transition from the active position to the inactive position is obtained by buckling of the membrane.
  • the solution of the invention therefore consists in modifying the exposure of the heat conducting element with respect to the first fluid so as to reduce the resistance to flow that it generates.
  • the term "buckling of the membrane” means that the membrane is subjected to a force, preferably of compression, which causes a bending and a deformation of the membrane in general in a direction perpendicular to the direction of application. force (transition from a state of compression to a state of bending).
  • Said element is preferably prestressed in compression, along an axis substantially parallel to an axis about which the bending of the membrane takes place during its buckling.
  • the heat conducting element is in the form of a blade.
  • the blade is secured to the membrane by a connecting edge and, in the active position, spaced apart from the membrane so as to be in contact with the first fluid by its two faces.
  • the blade in the inactive position is disposed by a face near the membrane.
  • the blade is preferably in contact with the first fluid only by a face which reduces the heat exchange with the fluid.
  • the blade has in active position a curved shape deviating from the membrane from the connecting edge.
  • heat exchange is controlled simply and efficiently.
  • the connecting edge is rectilinear and the blade is curved around the connecting edge in the active position.
  • the transition from the active position to the inactive position is obtained by deformation of the membrane along the connecting edge of the blade to the membrane.
  • the deformation of the blade support membrane induces a blade deformation between two states: a first state where the blade is curved in a direction parallel to the line formed by the connecting edge and a second state where the blade is curved perpendicular to the connecting edge.
  • the blade marries the membrane when the latter is in the form of a cylinder portion.
  • the deformation of the membrane is obtained by applying a force parallel to the plane of the membrane.
  • This force is advantageously a compressive force.
  • This deformation is preferably obtained by the force of a piston member.
  • the invention also relates to the application of the heat exchanger to the cooling of a fluid in a turbine engine, such as a turbojet engine.
  • a turbojet engine comprises an upstream air intake duct through which air is drawn into the engine and a downstream nozzle through which the hot gases produced by the combustion of a fuel are ejected for provide some of the thrust, at least. Between the inlet sleeve and the gas ejection nozzle, the sucked air is compressed by compression means, heated and expanded in turbines which drive the compression means.
  • the multi-flow turbojets additionally comprise at least one blower rotor displacing a large mass of air, forming the secondary flow and providing the bulk of the thrust, the primary flow being the part of the intake air flow which is heated then relaxed in the turbine, before being ejected through the primary flow nozzle.
  • the turbojet of the figure 1 is double flow and double body with successively in the direction of the path of the air in the engine, an air inlet 1 upstream, a blower 2 delivering air in an annular secondary flow channel 3 and to the flow compressors 4 primary in the center, the combustion chamber 5, and the turbine stages 6.
  • the secondary flow is ejected separately through a secondary flow nozzle.
  • the rotors are supported by the exhaust casing 7.
  • the primary flow is ejected through the primary flow nozzle 8 downstream of the exhaust casing.
  • the flow is annular and the vein of the primary flow is delimited internally by the exhaust cone 9.
  • the cone 9 is a hollow part of substantially frustoconical shape, integral with the exhaust casing.
  • a heat exchanger 10 in the secondary vein 3 for the purpose of cooling a fluid which may be air taken from the compressor.
  • An example of exchanger capable of performing this function comprises a circuit in which the fluid to be cooled circulates. This circuit is in thermal contact with a heat exchange membrane with the cold fluid circulating in the secondary vein. Fines are generally provided on the membrane on the side of the exchange surface facing the cold flow to increase the heat exchange capacity and improve cooling. These fins extend perpendicularly to the membrane in the secondary flow and create a pressure drop therein.
  • the exchanger 10 of the invention is represented on the Figures 2 to 6 . It comprises a box with a bottom wall 11, a plurality of partitions 13 perpendicular to the bottom wall 11 and delimiting between them and the bottom a plurality of channels 12 parallel to each other. These channels are covered with membranes 15 and communicate with a first manifold 12a at one end and a second manifold 12b at the other end of the box.
  • the box is supplied with fluid by the first collector. After circulating in the channels 12, the fluid can be recovered by the second collector 12b at the other end of the box.
  • the box is intended to be placed here along the secondary vein 3 of the turbojet, so that the membranes are in contact with a fluid at a different temperature for a heat exchange between the fluid flowing in the channels and the sweeping fluid the outer surface of the membranes.
  • the fluid flowing outside the channels is the first fluid and the fluid flowing in the channels is the second fluid.
  • the first fluid is the cold secondary flow and the second fluid is the fluid to be cooled.
  • the membranes 15 To improve the heat exchange between the two fluids of the heat conducting elements 17 are mounted on the membranes 15 on the side of the first fluid; it is metal blades 171 with a large contact surface for a small footprint. These blades 171 are fixed to the membranes 15 along a connecting edge 173 by welding or brazing, for example. Their two faces of larger dimensions of the blades 171 constitute the main heat exchange surfaces with the first fluid in which they are immersed.
  • the connecting edges are parallel to the direction of flow of the fluid with which the blades are in heat exchange.
  • these blades 171 are movable between an active position where they are raised with respect to the membrane which supports them and an inactive position where they are folded against the membrane. By being erect they have their two sides to the first fluid for maximum heat transfer between the two fluids. In the inactive position, the blades 171 being pressed against the membrane or at least extended along it have a lower heat exchange capacity than in the active position because the exchange surface is limited to one side of the blade. The flow resistances are also lower than in the active position for the same reason.
  • One aspect of the invention is the means for passing the blades 171 from one position to another.
  • the membranes 15 covering the channels 12 are fixed on one side 151 along a partition 13, and the other on the opposite partition 13. These membranes 15 are integral with a piston element 153.
  • the piston element 153 is movable inside a chamber 131 of cylinder arranged along the partition.
  • the piston is movable parallel to the plane of the membrane, in a direction transverse to the channels 12.
  • the movement of the piston is controlled by a control fluid supplied by a conduit 133 at the inlet of the chamber.
  • the piston formed of the piston and the cylinder chamber comprises any motor member capable of exerting a compressive force on the membrane parallel to its plane.
  • the actuating energy of the drive member or the jack may be pressurized air taken for example from the last stages of the compressor.
  • the membrane 15 is selected from a material which is preferably metallic for its heat conduction and resilience properties.
  • the membrane is arranged so that it can be deformed by the displacement of the piston between a first position where it is not subjected to a pressure of the control fluid and a second position where it is pushed back by the control fluid. introduced into the cylinder chamber. In the first position of the piston the membrane is flat as seen on the figure 2 . In the second position the membrane is curved as seen on the figure 3 . It took a cylinder-shaped form.
  • the heat conducting elements 17 are also made of a material which is preferably metallic for its heat conduction and resilience properties.
  • Non-limiting examples of materials are aluminum or a nickel-based alloy.
  • Aluminum is preferentially chosen for temperatures below 200 ° C. and nickel-based alloys such as Inconel® for higher temperatures.
  • the blades 171 forming the elements 17 have a curved shape around the connecting edge of the blades 171 with the membrane. This curved shape is obtained by plastic deformation around an axis parallel to the line of the connecting edge.
  • the blade is a laminar composite made of a stack of two sheets, one of the two sheets having been heated before being glued to the second. After returning to ambient temperature and after bonding, the composite blade is prestressed. This example is not limiting. A simple folded or stamped blade is suitable in that it is likely to take both positions.
  • the membrane 15 covering the channels 12 is provided with a plurality of blades 171 fixed along connecting edges perpendicular to the direction of the channels.
  • the membrane At rest when not subject to the control fluid, the membrane is flat and the connecting edges are straight.
  • the blades 171 are then in their rest form and curved around the connecting edges 173.
  • Such an exchanger can be used inside the secondary vein of a turbojet engine.
  • the cold air of the vein is the first fluid.
  • the fluid to be cooled is circulated inside the channels, forming the second fluid.
  • the membrane of the heat exchanger is kept flat, the heat conducting elements are then in the active position.
  • the control fluid is introduced into the cylinder chamber causing the displacement of the piston, the deformation of the membrane and the change of curvature of the blades; they take an inactive position.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Separation Using Semi-Permeable Membranes (AREA)
EP15790610.8A 2014-10-30 2015-10-23 Echangeur de chaleur et turbomoteur comportant un tel echangeur Active EP3213025B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1460461A FR3028021B1 (fr) 2014-10-30 2014-10-30 Echangeur de chaleur turbomoteur comportant un tel echangeur
PCT/FR2015/052855 WO2016066935A1 (fr) 2014-10-30 2015-10-23 Echangeur de chaleur et turbomoteur comportant un tel echangeur

Publications (2)

Publication Number Publication Date
EP3213025A1 EP3213025A1 (fr) 2017-09-06
EP3213025B1 true EP3213025B1 (fr) 2018-12-12

Family

ID=52737186

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15790610.8A Active EP3213025B1 (fr) 2014-10-30 2015-10-23 Echangeur de chaleur et turbomoteur comportant un tel echangeur

Country Status (8)

Country Link
US (1) US10739086B2 (ru)
EP (1) EP3213025B1 (ru)
CN (1) CN107110623B (ru)
BR (1) BR112017008463B1 (ru)
CA (1) CA2965396C (ru)
FR (1) FR3028021B1 (ru)
RU (1) RU2689238C2 (ru)
WO (1) WO2016066935A1 (ru)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3082237B1 (fr) * 2018-06-12 2020-10-30 Safran Aircraft Engines Dispositif d'echange de chaleur a faibles pertes de charge
FR3095264B1 (fr) 2019-04-17 2021-03-19 Safran Aircraft Engines Echangeur de chaleur air secondaire/fluide, son procédé de fabrication et turbomachine à double flux équipée de cet échangeur
US11834993B1 (en) * 2023-03-29 2023-12-05 Pratt & Whitney Canada Corp. Engine exhaust reverse flow prevention
US12044173B1 (en) 2023-04-28 2024-07-23 Pratt & Whitney Canada Corp. Engine exhaust reverse flow prevention

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JPS61186785A (ja) * 1985-02-15 1986-08-20 Matsushita Electric Works Ltd 熱搬送器
US4773593A (en) * 1987-05-04 1988-09-27 United Technologies Corporation Coolable thin metal sheet
RU2193732C2 (ru) * 2000-09-27 2002-11-27 Открытое акционерное общество "Концерн Стирол" Устройство для создания устойчивого к рассеиванию потока горячих газообразных выбросов
US7235914B2 (en) * 2000-10-25 2007-06-26 Washington State University Research Foundation Piezoelectric micro-transducers, methods of use and manufacturing methods for same
US6628522B2 (en) * 2001-08-29 2003-09-30 Intel Corporation Thermal performance enhancement of heat sinks using active surface features for boundary layer manipulations
CN101285403A (zh) * 2008-01-18 2008-10-15 北京航空航天大学 涡轮叶片微通道内部冷却系统的气流通道结构
US20090223648A1 (en) * 2008-03-07 2009-09-10 James Scott Martin Heat exchanger with variable heat transfer properties
FR2930324B1 (fr) * 2008-04-17 2011-06-17 Snecma Dispositif de refroidissement d'une paroi
US7926471B2 (en) * 2008-06-24 2011-04-19 GM Global Technology Operations LLC Heat exchanger with variable turbulence generators
US8339787B2 (en) * 2010-09-08 2012-12-25 Apple Inc. Heat valve for thermal management in a mobile communications device
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Also Published As

Publication number Publication date
US10739086B2 (en) 2020-08-11
FR3028021A1 (fr) 2016-05-06
CN107110623B (zh) 2019-03-26
RU2017114973A3 (ru) 2019-04-04
CN107110623A (zh) 2017-08-29
EP3213025A1 (fr) 2017-09-06
FR3028021B1 (fr) 2019-03-22
BR112017008463A2 (pt) 2018-01-09
RU2689238C2 (ru) 2019-05-24
US20170321972A1 (en) 2017-11-09
CA2965396A1 (fr) 2016-05-06
BR112017008463B1 (pt) 2021-03-23
WO2016066935A1 (fr) 2016-05-06
CA2965396C (fr) 2023-01-17
RU2017114973A (ru) 2018-11-30

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