WO2021192599A1 - Film thermoconducteur, dispositif de chauffage et moteur à turbines à gaz - Google Patents

Film thermoconducteur, dispositif de chauffage et moteur à turbines à gaz Download PDF

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Publication number
WO2021192599A1
WO2021192599A1 PCT/JP2021/003075 JP2021003075W WO2021192599A1 WO 2021192599 A1 WO2021192599 A1 WO 2021192599A1 JP 2021003075 W JP2021003075 W JP 2021003075W WO 2021192599 A1 WO2021192599 A1 WO 2021192599A1
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WO
WIPO (PCT)
Prior art keywords
heat conductive
conductive film
plane direction
nacelle
gas turbine
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/JP2021/003075
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English (en)
Japanese (ja)
Inventor
航介 池田
直元 石川
竹史 船津
大山　健一
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.)
Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries 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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of WO2021192599A1 publication Critical patent/WO2021192599A1/fr
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Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B6/00—Heating by electric, magnetic or electromagnetic fields
    • H05B6/02—Induction heating
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B6/00—Heating by electric, magnetic or electromagnetic fields
    • H05B6/02—Induction heating
    • H05B6/10—Induction heating apparatus, other than furnaces, for specific applications

Definitions

  • the present disclosure relates to heat conductive films, heating devices and gas turbine engines.
  • a composite material including an insulating layer, a conductive layer, and a heat conductive layer is known (see, for example, Patent Document 1).
  • the heat conductive layer contains a resin and hexagonal boron nitride.
  • hexagonal boron nitride as a heat conductive filler generates heat when an electric current is passed through the conductive layer.
  • the nacelle part of the gas turbine engine of an aircraft is provided with an anti-icing device to suppress icing.
  • the nacelle is constructed using a composite material.
  • the anti-icing device for example, it is conceivable to use the composite material of Patent Document 1.
  • the composite material of Patent Document 1 functions as a heat conductive film.
  • the heat conductive film has a low thermal conductivity in the laminating direction, so that the surface temperature of the composite material is required. It is difficult to raise it to.
  • the heat conductive film of the present disclosure includes a graphene sheet extending in the in-plane direction and a resin sheet provided by laminating the graphene sheet in the out-of-plane direction orthogonal to the in-plane direction.
  • a plurality of the resin sheets are laminated and formed into a sheet shape with the in-plane direction or the out-of-plane direction as the thickness direction.
  • the heating device of the present disclosure is provided on one surface side of a composite material to be heated, and on the other surface side of the heat conductive film according to claim 1 or 2, sandwiching the composite material. , A heating unit for heating the heat conductive film.
  • the gas turbine engine of the present disclosure is a gas turbine engine including the above heating device as an anti-icing device, and is provided with an engine main body, a nacelle for storing the engine main body, and the anti-icing device provided on the intake side of the nacelle.
  • the nacelle is provided with an intake port that is an annular opening on the intake side, and the anti-icing device has a first heat conductive film provided on the upstream end surface of the intake port.
  • the first heat conductive film is provided in an annular shape along the circumferential direction of the intake port, which has an out-of-plane direction in the thickness direction and is annular.
  • heat transfer having directivity can be performed.
  • FIG. 1 is a perspective view schematically showing an aircraft equipped with the anti-icing device according to the first embodiment.
  • FIG. 2 is a one-sided cross-sectional view schematically showing the periphery of the nacelle provided with the anti-icing device according to the first embodiment.
  • FIG. 3 is an explanatory diagram showing an example of the heat conductive film according to the first embodiment.
  • FIG. 4 is a front view of the nacelle as viewed from the intake side.
  • FIG. 5 is a cross-sectional view taken along the line AA of FIG. 4 schematically showing a heat conductive film provided on the nacelle.
  • FIG. 6 is an explanatory diagram showing an example of the heat conductive film according to the second embodiment.
  • FIG. 7 is a graph showing changes in the in-plane direction and the out-of-plane direction of the heat conductive film according to the second embodiment.
  • FIG. 8 is a cross-sectional view showing an example of the heat conductive film according to the third embodiment.
  • FIG. 1 is a perspective view schematically showing an aircraft equipped with the anti-icing device according to the first embodiment.
  • FIG. 2 is a one-sided cross-sectional view schematically showing the periphery of the nacelle provided with the anti-icing device according to the first embodiment.
  • FIG. 3 is an explanatory diagram showing an example of the heat conductive film according to the first embodiment.
  • FIG. 4 is a front view of the nacelle as viewed from the intake side.
  • FIG. 5 is a cross-sectional view taken along the line AA of FIG. 4 schematically showing a heat conductive film provided on the nacelle.
  • the heat conductive film 21 according to the first embodiment is applied to an anti-icing device 20 that suppresses icing in the nacelle 11 of the gas turbine engine 10 of the aircraft 1.
  • Aircraft 1 will be described with reference to FIG.
  • Aircraft 1 includes an airframe 5 and a gas turbine engine 10 attached to a main wing 6 of the airframe 5.
  • the gas turbine engine 10 is a thrust generator that generates the thrust of the aircraft 1.
  • the gas turbine engine 10 includes a nacelle 11, an engine body 12, and an anti-icing device 20.
  • the nacelle 11 stores the engine body 12.
  • the nacelle 11 is provided on the outside of the engine body 12 and is a casing that covers the engine body 12.
  • the nacelle 11 is formed in a cylindrical shape, and an intake port 15 and an exhaust port (not shown) are formed.
  • the intake port 15 has a circular opening.
  • the nacelle 11 is constructed using a composite material containing a resin and reinforcing fibers.
  • the anti-icing device 20 is provided on the intake side of the nacelle 11.
  • the anti-icing device 20 is a heating device that heats and melts the ice adhering around the intake port 15 of the nacelle 11.
  • the shape of the portion on the intake side of the nacelle 11 on which the anti-icing device 20 is provided will be described.
  • the portion of the nacelle 11 on the intake side is formed in a ring shape so as to form an intake port 15 having a circular opening.
  • the portion of the nacelle 11 on the intake side is formed in a U shape in a cross section cut along a plane orthogonal to the circumferential direction. That is, the cross-sectional shape of the intake side portion of the nacelle 11 has the intake side as the top, one end extending toward the exhaust side of the inner peripheral surface, and the other end toward the exhaust side of the outer peripheral surface. Is postponed.
  • the anti-icing device 20 includes a plurality of heat conductive films 21, an induction heating unit 22, and a power supply 23.
  • the heat conductive film 21 is a film having directivity in the direction of heat transfer. As shown in FIG. 3, the heat conductive film 21 is formed by alternately laminating graphene sheets 25 and resin sheets 26.
  • the graphene sheet 25 is formed in a sheet shape extending in a predetermined in-plane direction, and the direction of heat transfer is the in-plane direction.
  • the resin sheet 26 is formed in the form of a sheet extending in a predetermined in-plane direction, and is composed of a thermoplastic resin or a thermosetting resin.
  • the graphene sheet 25 and the resin sheet 26 are laminated in the out-of-plane direction.
  • the heat conductive film 21 generates heat when the graphene sheet 25 is induced and heated by the induction heating unit 22.
  • the directivity of the heat conductive film 21 in the direction of heat transfer changes depending on whether the thickness direction of the laminated graphene sheet 25 and the resin sheet 26 is the in-plane direction or the out-of-plane direction.
  • FIG. 3 shows three-dimensional coordinates including the X direction, the Y direction, and the Z direction.
  • the thickness direction of the heat conductive film 21 is the Z direction, and the graphene sheet 25 and the resin sheet 26 are laminated in the Z direction. That is, the thickness direction of the heat conductive film 21 is the out-of-plane direction of the laminated graphene sheet 25 and the resin sheet 26.
  • the heat conductive film 21 is difficult to transfer heat in the X direction and the Y direction on the heating surface, and transfers heat in the Z direction. do.
  • the thickness direction of the heat conductive film 21 is the Z direction, and the graphene sheet 25 and the resin sheet 26 are laminated in the Y direction. That is, the thickness direction of the heat conductive film 21 is the in-plane direction of the XZ planes of the laminated graphene sheet 25 and the resin sheet 26.
  • the heat conductive film 21 transfers heat in the X direction and the Z direction on the heating surface, but it is difficult to transfer heat in the Y direction. It has become.
  • the thickness direction of the heat conductive film 21 is the Z direction, and the graphene sheet 25 and the resin sheet 26 are laminated in the X direction. That is, the thickness direction of the heat conductive film 21 is the in-plane direction of the YZ plane of the laminated graphene sheet 25 and the resin sheet 26.
  • the heat conductive film 21 transfers heat in the Y direction and the Z direction on the heating surface, but it is difficult to transfer heat in the X direction. It has become.
  • a plurality of heat conductive films 21 as described above are arranged on the outer surface side of the nacelle 11. Specifically, the plurality of heat conductive films 21 are provided on both sides (downstream side) of the first heat conductive film 21a provided on the top portion (single point chain line in FIG. 4) on the intake side and the first heat conductive film 21a.
  • the second heat conductive film 21b to be obtained is included.
  • the first heat conductive film 21a is provided on the upstream end surface of the intake port 15 and is arranged along the top of the intake side to form an annular shape as shown in FIG.
  • the thickness direction of the first heat conductive film 21a is the direction connecting the inner surface and the outer surface of the nacelle 11, and the laminating direction of the graphene sheet 25 and the resin sheet 26 is along the outer surface of the nacelle 11.
  • the direction is the direction connecting the inner peripheral surface and the outer peripheral surface of the nacelle 11. Therefore, the first heat conductive film 21a having an annular shape transfers heat in the circumferential direction on the outer surface of the nacelle 11.
  • the second heat conductive film 21b has a substantially cylindrical shape by being arranged along the inner peripheral surface side and the outer peripheral surface side, respectively.
  • the thickness direction of the second heat conductive film 21b is the direction connecting the inner surface and the outer surface of the nacelle 11, and the graphene sheet 25 and the resin sheet 26 are laminated in the inner and outer surfaces of the nacelle 11. It is the direction to connect. Therefore, the second heat conductive film 21b, which has a substantially cylindrical shape, transfers heat on the outer surface of the nacelle 11 in the direction connecting the inner surface and the outer surface.
  • the induction heating unit 22 is provided on the opposite side of the heat conductive film 21 with the nacelle 11 interposed therebetween.
  • the induction heating unit 22 heats the heat conductive film 21 by induction heating.
  • the induction heating unit 22 irradiates the heat conductive film 21 with, for example, a high-frequency electromagnetic wave.
  • the power supply 23 is electrically connected to the induction heating unit 22 and applies a voltage to the induction heating unit 22.
  • the power supply 23 applies a high frequency voltage to the induction heating unit 22.
  • the above-mentioned anti-icing device 20 irradiates the heat conductive film 21 with high-frequency electromagnetic waves from the induction heating unit 22 by applying a high-frequency voltage from the power supply 23 to the induction heating unit 22.
  • the heat conductive film 21 When the heat conductive film 21 is irradiated with high-frequency electromagnetic waves, it generates heat due to induction heating.
  • the ring-shaped first heat conductive film 21a transfers heat in the circumferential direction to raise the temperature of the intake port 15 of the nacelle 11 along the circumferential direction.
  • cylindrical second heat conductive film 21b transfers heat from the inside toward the inner peripheral surface side and from the inner side toward the outer peripheral surface, thereby transmitting heat to the inner peripheral surface on the intake side of the nacelle 11 and the inner peripheral surface.
  • the temperature of the outer peripheral surface is raised along the circumferential direction.
  • FIG. 6 is an explanatory diagram showing an example of the heat conductive film according to the second embodiment.
  • FIG. 7 is a graph showing changes in the in-plane direction and the out-of-plane direction of the heat conductive film according to the second embodiment.
  • the heat conductive film (first heat conductive film) 27 is provided on the outer surface side of the nacelle 11, and the heat conductive film 27 is laminated in the direction from the top of the nacelle 11 to both sides thereof. It changes continuously.
  • the Z direction is the thickness direction of the heat conductive film 27, and the X direction is an orthogonal direction orthogonal to the thickness direction.
  • the heat conductive film 27 of the second embodiment is at the top of the nacelle 11 on the intake side, and the graphene sheet 25 and the resin sheet 26 are laminated in a direction perpendicular to the heat conductive film 21. It has become. That is, the laminating direction of the graphene sheet 25 and the resin sheet 26 is the X direction, and the angle ⁇ formed by the laminating direction with respect to the X direction is 0 °. In other words, since the graphene sheet 25 and the resin sheet 26 are laminated in the X direction, the angle ⁇ formed by the stacking direction with respect to the Z direction is 90 °.
  • the graphene sheet 25 and the resin sheet 26 are laminated in a direction along the thickness direction of the heat conductive film 27. It has become. That is, the graphene sheet 25 and the resin sheet 26 are laminated in the Z direction, and the angle ⁇ formed by the stacking direction with respect to the X direction is 90 °. In other words, since the graphene sheet 25 and the resin sheet 26 are laminated in the Z direction, the angle ⁇ formed by the stacking direction with respect to the Z direction is 0 °.
  • the vertical axis thereof is the value of sin ⁇ based on the angle ⁇ formed by the stacking direction with respect to the X direction or Z.
  • the horizontal axis thereof is a position, the position of the top of the nacelle 11 on the intake side is zero, and the positions of the ends on both sides (away from the top) of the nacelle 11 are L.
  • the heat conductive film 27 is continuously displaced so that the value of sin ⁇ (dotted line) changes from 0 to 1 as the stacking direction with respect to the X direction goes from the top to the end.
  • the heat conductive film 27 is continuously displaced so that the value of sin ⁇ (solid line) becomes 1 to 0 as the stacking direction with respect to the Z direction goes from the top to the end.
  • the heat conductive film 27 of the second embodiment preferably transfers heat in the circumferential direction of the nacelle 11 by continuously displacing the laminating direction from the top to the end of the nacelle 11. be able to.
  • FIG. 8 is a cross-sectional view showing an example of the heat conductive film according to the third embodiment.
  • the heat conductive film 31 of the third embodiment further includes an adhesive layer 32 between the graphene sheet 25 and the resin sheet 26 of the heat conductive films 21 of the first and second embodiments.
  • the adhesive layer 32 joins the graphene sheet 25 and the resin sheet 26 and functions as a heat insulating layer. Therefore, in the heat conductive film 31, the heat transfer in the laminating direction is suppressed by the adhesive layer 32, so that the heat can be easily transferred in the in-plane direction, and the directivity in the heat transfer direction can be improved. It will be possible to increase it further.
  • the heat conductive films 21, 31 and the heating device (ice-proof device 20) and the gas turbine engine 10 described in the embodiment are grasped as follows, for example.
  • the heat conductive films 21 and 31 according to the first aspect are a resin sheet 26 provided by laminating a graphene sheet 25 extending in the in-plane direction and the graphene sheet 25 in the out-of-plane direction orthogonal to the in-plane direction.
  • the graphene sheet 25 and the resin sheet 26 are laminated in plurality, and are formed in a sheet shape with the in-plane direction or the out-of-plane direction as the thickness direction.
  • directivity can be given in the direction of heat transfer. Therefore, since the heat conductive film 21 having directivity can be arranged according to the mode of the object to be heated, it is possible to efficiently raise the temperature by heating the heat conductive film 21.
  • an adhesive layer 32 provided between the graphene sheet 25 and the resin sheet 26 is further provided in the out-of-plane direction.
  • the adhesive layer 32 functions as a heat insulating layer, so that the directivity related to the heat transfer of the heat conductive film 21 can be further improved.
  • the heating device (ice-proof device 20) is the heat conductive films 21 and 31 provided on one side of the composite material (nacell 11) to be heated, and the composite material.
  • a heating unit (induction heating unit 22) for heating the heat conductive films 21 and 31 is provided on the other surface side of the film.
  • the heating unit is the induction heating unit 22, but it may be a magnetic field heating unit that performs magnetic field heating.
  • the gas turbine engine 10 is a gas turbine engine 10 including the above heating device as an ice prevention device 20, and includes an engine body 12, a nacelle 11 for storing the engine body 12, and the nacelle 11.
  • the nacelle 11 is provided with an intake port 15 which is an annular opening on the intake side, and the ice prevention device 20 is provided on the upstream side of the intake port 15.
  • the first heat conductive film 21a provided on the end face is provided, and the thickness direction of the first heat conductive film 21a is the out-of-plane direction, and the first heat conductive film 21a is in the circumferential direction of the intake port 15 which is annular. It is provided in a ring along the line.
  • the adhesion of ice on the intake side in the nacelle 11 of the gas turbine engine 10 can be quickly heated and melted by the anti-icing device 20.
  • the anti-icing device 20 further includes a second heat conductive film 21b provided on the downstream side of the first heat conductive film 21a, and the second heat conductive film 21b is formed by the second heat conductive film 21b.
  • the thickness direction is the in-plane direction, and the intake port 15 is provided in an annular shape along the circumferential direction of the intake port 15.
  • the ice that could not be completely melted by the first heat conductive film 21a can be melted by the second heat conductive film 21b.
  • the first heat conductive film 27 is continuously displaced in the out-of-plane direction (lamination direction) with respect to the thickness direction as the distance from the intake port 15 of the nacelle 11 increases.
  • the first heat conductive film 27 preferably displaces the laminating direction of the first heat conductive film 27 in a predetermined direction of the nacelle 11 by continuously displacing the laminating direction as the distance from the intake port 15 of the nacelle 11 increases. It can be carried out.
  • Aircraft Aircraft 5 Airframe 6 Main wings 10 Gas turbine engine 11 Nacelle 12 Engine body 15 Intake port 20 Anti-icing device 21 Heat conduction film (Embodiment 1) 22 Induction heating unit 23 Power supply 25 Graphene sheet 26 Resin sheet 27 Heat conductive film (Embodiment 2) 31 Thermal conductive film (Embodiment 3) 32 Adhesive layer

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Laminated Bodies (AREA)
  • General Induction Heating (AREA)
  • Wind Motors (AREA)
  • Carbon And Carbon Compounds (AREA)

Abstract

Film thermoconducteur comprenant une feuille de graphène s'étendant dans le sens dans le plan et une feuille de résine obtenue en étant stratifiée dans le sens hors plan orthogonal vers le sens dans le plan de la feuille de graphène, une pluralité de feuilles de graphène et de feuilles de résine étant stratifiées et également formées sous une forme de feuille avec le sens dans le plan ou le sens hors du plan comme sens de l'épaisseur. Le film thermoconducteur peut en outre comprendre une couche adhésive disposée entre la feuille de graphène et la feuille de résine dans le sens hors plan. En outre, un dispositif de chauffage comprend le film thermoconducteur disposé sur un côté de surface du matériau composite à chauffer, et une unité de chauffage qui est disposée sur l'autre côté de surface du matériau composite et chauffe le film thermoconducteur.
PCT/JP2021/003075 2020-03-27 2021-01-28 Film thermoconducteur, dispositif de chauffage et moteur à turbines à gaz Ceased WO2021192599A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2020-058962 2020-03-27
JP2020058962A JP2021158029A (ja) 2020-03-27 2020-03-27 熱伝導フィルム、加熱装置及びガスタービンエンジン

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WO2021192599A1 true WO2021192599A1 (fr) 2021-09-30

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PCT/JP2021/003075 Ceased WO2021192599A1 (fr) 2020-03-27 2021-01-28 Film thermoconducteur, dispositif de chauffage et moteur à turbines à gaz

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115165959A (zh) * 2022-07-07 2022-10-11 广东墨睿科技有限公司 热模拟测试方法、设备和系统
WO2023111469A1 (fr) * 2021-12-17 2023-06-22 Safran Nacelles Levre d'entree d'air pour une nacelle d'un ensemble propulsif d'aeronef

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011023670A (ja) * 2009-07-17 2011-02-03 Thermo Graphitics Co Ltd 異方性熱伝導素子及びその製造方法
EP3153409A1 (fr) * 2015-10-05 2017-04-12 Airbus Defence and Space, S.A. Dispositif et procédé de protection contre le givre
JP2017071079A (ja) * 2015-10-05 2017-04-13 積水化学工業株式会社 熱伝導シート、熱伝導シート積層体及び熱伝導シート成形体
WO2018159909A1 (fr) * 2017-02-28 2018-09-07 서울대학교산학협력단 Système de chauffage et élément chauffant

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011023670A (ja) * 2009-07-17 2011-02-03 Thermo Graphitics Co Ltd 異方性熱伝導素子及びその製造方法
EP3153409A1 (fr) * 2015-10-05 2017-04-12 Airbus Defence and Space, S.A. Dispositif et procédé de protection contre le givre
JP2017071079A (ja) * 2015-10-05 2017-04-13 積水化学工業株式会社 熱伝導シート、熱伝導シート積層体及び熱伝導シート成形体
WO2018159909A1 (fr) * 2017-02-28 2018-09-07 서울대학교산학협력단 Système de chauffage et élément chauffant

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023111469A1 (fr) * 2021-12-17 2023-06-22 Safran Nacelles Levre d'entree d'air pour une nacelle d'un ensemble propulsif d'aeronef
US12398657B2 (en) 2021-12-17 2025-08-26 Safran Nacelles Air intake lip for a nacelle of an aircraft propulsion assembly
CN115165959A (zh) * 2022-07-07 2022-10-11 广东墨睿科技有限公司 热模拟测试方法、设备和系统
CN115165959B (zh) * 2022-07-07 2023-05-02 广东墨睿科技有限公司 热模拟测试方法、设备和系统

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