EP3519753B1 - Matrix für einen luft-öl-wärmetauscher eines strahltriebwerks - Google Patents

Matrix für einen luft-öl-wärmetauscher eines strahltriebwerks Download PDF

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Publication number
EP3519753B1
EP3519753B1 EP17772077.8A EP17772077A EP3519753B1 EP 3519753 B1 EP3519753 B1 EP 3519753B1 EP 17772077 A EP17772077 A EP 17772077A EP 3519753 B1 EP3519753 B1 EP 3519753B1
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EP
European Patent Office
Prior art keywords
fluid
matrix
fins
heat exchanger
flow
Prior art date
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Application number
EP17772077.8A
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English (en)
French (fr)
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EP3519753A1 (de
Inventor
Vincent Thomas
Bruno Servais
Roel VLEUGELS
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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Publication of EP3519753A1 publication Critical patent/EP3519753A1/de
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Classifications

    • 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
    • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D7/16—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D7/16—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
    • F28D7/163—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation with conduit assemblies having a particular shape, e.g. square or annular; with assemblies of conduits having different geometrical features; with multiple groups of conduits connected in series or parallel and arranged inside common casing
    • F28D7/1638—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation with conduit assemblies having a particular shape, e.g. square or annular; with assemblies of conduits having different geometrical features; with multiple groups of conduits connected in series or parallel and arranged inside common casing with particular pattern of flow or the heat exchange medium flowing inside the conduits assemblies, e.g. change of flow direction from one conduit assembly to another one
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
    • F28F1/126—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element consisting of zig-zag shaped 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
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
    • F28F1/34—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending obliquely
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
    • F28F1/38—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and being staggered to form tortuous fluid passages
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2250/00—Arrangements for modifying the flow of the heat exchange media, e.g. flow guiding means; Particular flow patterns
    • F28F2250/10—Particular pattern of flow of the heat exchange media

Definitions

  • the invention relates to the field of turbomachine heat exchangers. More specifically, the invention provides a heat exchanger matrix.
  • the invention further provides a method for producing such a heat exchanger matrix.
  • the invention also relates to a turbomachine equipped with such a heat exchanger matrix.
  • the document US 2015/0345396 A1 discloses a turbofan engine with a heat exchanger.
  • This heat exchanger equips a blade wall in order to cool it.
  • the heat exchanger comprises a body in which is formed a vascular structure allowing the passage of a cooling fluid through the body.
  • the vascular structure is in the form of nodes connected by branches, these nodes and these branches being hollowed out so as to provide interconnecting passages through the body.
  • the document US 1,990,541A shows a heat exchanger matrix according to the preamble of claim 1.
  • the object of the invention is to solve at least one of the problems posed by the prior art.
  • the object of the invention is to optimize the heat exchange, the pressure drops, and possibly the operation of a turbomachine.
  • the invention also aims to provide a solution that is simple, strong, light, economical, reliable, easy to produce, easy to maintain, easy to inspect, and improves performance.
  • the subject of the invention is a heat exchanger matrix between a first fluid and a second fluid, according to the subject of claim 1.
  • the invention also relates to a heat exchanger matrix with heat exchange fins, remarkable in that it comprises a helical passage formed between the fins, optionally several coaxial helical passages which are formed between the fins.
  • the coaxial helical passages have the same pitch, and/or the same radius.
  • the invention also relates to a heat exchanger matrix between a first fluid and a second fluid, the matrix comprising: a passage for the flow of the first fluid in a general direction; a network extending in the bushing and in which the second fluid circulates; at least two successive fins in the general direction of the first fluid which extend from the network; remarkable in that between the two successive fins, the matrix comprises a passage oriented transversely with respect to the general direction of the first fluid; and/or said successive fins are joined to the same network portion at junctions offset transversely in the general direction.
  • the invention also relates to a matrix for a heat exchanger between a first fluid and a second fluid, in particular a matrix for a heat exchanger for a turbomachine, the matrix comprising: a passage for the flow of the first fluid according to a general sense; a network extending in the bushing and in which the second fluid circulates; remarkable in that the network supports at least two successive crosses which are arranged in the first fluid and which are pivoted relative to each other.
  • the successive crosses are formed of successive fins.
  • the successive crosses are pivoted relative to each other by at least 5°, or 10° or 20°.
  • the invention also relates to a matrix for a heat exchanger comprising at least two passages for a first fluid between which is arranged a spacing which can be traversed by a second fluid moving along a main direction, the spacing being provided with at least two non-parallel fins each connecting the first passage to the second passage, characterized in that, seen in a plane perpendicular to the main direction of flow of the second fluid, the fins intersect at at least one point of the distinct spacing from the connection point of the fins to the passages.
  • the invention also relates to a turbomachine, in particular a turbojet comprising a heat exchanger with a matrix, bearings, and a transmission driving a fan, characterized in that the matrix is in accordance with the invention, preferably the heat exchanger heat is an oil-air heat exchanger.
  • the turbomachine comprises a circuit with oil forming the second fluid, said oil being in particular a lubricating and/or cooling oil.
  • the turbomachine comprises an air sampling sleeve, said air forming the first fluid.
  • the bearings and/or the transmission are supplied by the oil passing through the exchanger.
  • the heat exchanger has a generally arcuate shape; the tubes possibly being oriented radially.
  • the invention also relates to a method for producing a heat exchanger matrix between a first fluid and a second fluid, the matrix comprising: a passage for the flow of the first fluid; a network extending in the bushing and in which the second fluid circulates; the method comprising the following steps: (a) designing the heat exchanger with its matrix; (b) production of the matrix by additive manufacturing along a printing direction; remarkable in that step (b) production comprises the production of fins extending along main directions which are inclined with respect to the direction of printing, the matrix optionally being in accordance with the invention.
  • the fins are arranged in planes inclined relative to the printing direction by an angle ⁇ of between 20° and 60°, optionally of between 30° and 50°.
  • step (b) production comprises the production of tubes inclined relative to the printing direction by an angle of between 20° and 60°, optionally of between 30° and 50° .
  • step (b) production comprises the production of channels substantially parallel to the printing direction.
  • the invention also relates to an aircraft, in particular a jet aircraft, comprising a turbomachine and/or a heat exchanger matrix, noteworthy in that the matrix conforms to the invention, and/or the turbomachine conforms to the invention, and/or the matrix is manufactured according to a production method according to the invention.
  • the matrix is placed in the turbomachine, and/or in the fuselage, and/or in a wing of the aircraft.
  • each object of the invention is also applicable to the other objects of the invention.
  • each object of the invention can be combined with other objects.
  • the objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with each other.
  • the invention makes it possible to increase the heat exchange while limiting the pressure drops of the air flow.
  • this solution becomes particularly relevant since the cold source is at very low temperature in addition to being available in large quantities given the flow rate of the secondary flow. Not slowing down the flow of fresh air when it crosses the matrix promotes its renewal and limits its rise in temperature.
  • the fins and tubes downstream of the exchanger benefit from fresh air with an optimal temperature difference.
  • the inclination of the successive fins allows a better participation of the air in the heat exchange while limiting the necessary contact surface. This reduces the pressure losses, and in general the creation of entropy. Furthermore, the orientation of the passages between the fins increases the passage sections, but still reducing pressure drops.
  • connections formed by the fins make it possible to connect the tubes or the parts of the mesh. Thus, they optimize the mechanical resistance. Since these links are angled relative to each other, the overall stiffness is improved because some links work in compression while others work in compression.
  • upstream and downstream refer to the main flow direction of the flow in the exchanger.
  • the figure 1 schematically represents an axial turbomachine.
  • the turbojet engine 2 comprises a first compression level, called low-pressure compressor 5, a second compression level, called high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor 12 around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter until it enters the combustion chamber 8.
  • An inlet fan commonly referred to as a fan or blower 16 is coupled to the rotor 12 via a transmission 17. It generates an air flow which is divided into a primary flow 18 crossing the various aforementioned levels of the turbomachine, and a secondary flow 20 The secondary flow can be accelerated so as to generate a thrust reaction.
  • the transmission 17 and the bearings 22 of the rotor 12 are lubricated and cooled by an oil circuit. Its oil passes through a heat exchanger 24 placed in a sleeve 26 taking part of the secondary flow 20 used as a cold source.
  • the figure 2 shows a plan view of a heat exchanger 24 such as that shown in figure 1 .
  • the heat exchanger 24 has a generally arcuate shape. It marries an annular casing 28 of the turbomachine. It is crossed by the air of the secondary flow which forms a first fluid, and receives oil forming a second fluid. It comprises a matrix 30 disposed between two collectors 32 closing its ends and collecting the second fluid; for example the oil during its cooling.
  • the exchanger can be mixed and comprise both the two types of matrices described below.
  • the picture 3 sketches a front view of a heat exchanger matrix 30 according to the first embodiment of the invention.
  • the matrix 30 may correspond to that shown in figure 2 .
  • the matrix 30 has a passage allowing the first fluid to flow right through the matrix 30.
  • the flow can take place in a general direction, possibly perpendicular to the two opposite main faces.
  • the crossing can generally form a corridor; possibly of variable external contour.
  • a network receiving the second fluid is arranged in the bushing.
  • the network may comprise a series of tubes 34.
  • the various tubes 34 may provide passages 36 between them.
  • the tubes 34 support fins (38; 40). These fins (38; 40) can be placed one after the other according to the flow of the first fluid, so that they form successive fins according to this flow.
  • the concentration of fins in the matrix 30 can vary.
  • a first succession is shown with front fins 38 (shown in solid lines), and rear fins 40 (shown in dotted lines).
  • the front fins 38 are placed in a forward plane, and the rear fins 40 are placed in the background.
  • the fins (38; 40) are offset from one plane to another. By offset is meant a variation in inclination, and/or a deviation transverse to the flow of the first fluid.
  • offset is meant a variation in inclination, and/or a deviation transverse to the flow of the first fluid.
  • two successive fins (38; 40) can each extend into the first fluid along a specific main direction. These main directions can be inclined relative to each other, in particular inclined by 90°. From the front, the successive fins (38; 40) draw crosses, for example series of crosses connecting the tubes 34. Since the fins (38; 40) are inclined with respect to the tubes 34, they form triangulations, or legs of strength.
  • intersections 42 in the space of the successive fins (38; 40) are at a distance from the tubes 34, possibly halfway between two successive tubes 34. This central position of the intersections 42 avoids amplifying the losses in the boundary layers.
  • the figure 4 is cut along axis 4-4 drawn on the picture 3 . Being seen in section from intersections, the fins (38; 40) are visible in halves.
  • fins (38; 40) are shown one behind the other along the primary flow 20.
  • the fins (38; 40) extend from the partitions 48 forming the tubes 34. They can form flat tongues.
  • the tubes 34 are staggered in the section. They notably form horizontal lines, aligned along the secondary flow 20, or aligned along the flow of the first fluid.
  • the matrix 30 has an inlet 41 and an outlet 43.
  • the primary flow 20 borrows the matrix 30 from the inlet to the outlet, thus defining the direction of flow of the first fluid, possibly its main direction of flow.
  • the matrix 30 can comprise an outer casing 45.
  • the outer casing can form an outer skin of the matrix 30.
  • the outer casing 45 can delimit, in particular surround the bushing and/or the network.
  • Both the inlet 41 and the outlet 43 can be made in the outer casing 45.
  • the latter can form a support for the entities inside.
  • the partitions 48 of the tubes 34 form the structure of the matrix 30, the heat exchange taking place across their thicknesses.
  • the tubes 34 can be partitioned by an internal wall 35, which increases the rigidity of these tubes 34.
  • the interior of the tubes is decorated with obstacles (not shown) to generate eddies in the second fluid to increase heat exchange.
  • the fins (38; 40) of the different fin planes can be spaced apart from the other fins, which reduces the mass and the occupation of the passage.
  • the front fins 38 can join the upstream tubes, and the rear fins 40 join the tubes arranged downstream.
  • This configuration makes it possible to connect the tubes 34 to each other despite the presence of the passages 36 separating them.
  • the tubes 34 can have rounded profiles, for example in ellipses. They are thinned transversely to the flow of the first fluid to reduce pressure drops, and therefore increase the possible flow rate.
  • the tubes 34 placed in the extension of each other according to the flow of the first fluid are separated by the passages 36.
  • other passages 36 separate the superimposed tubes. Since these passages 36 communicate with each other, the matrix becomes through and the flow of the first fluid can travel in a straight line as well as diagonally with respect to the secondary flow 20.
  • the figure 5 shows a heat exchanger matrix 130 according to a second embodiment of the invention.
  • This figure 6 repeats the numbering of the preceding figures for the identical or similar elements, the numbering being however incremented by 100. Specific numbers are used for the elements specific to this embodiment.
  • the die 130 is shown from the front such that the flow of the first fluid encounters it when it enters the bushing.
  • the network forms a mesh 144, for example with tracks connected to each other by forming polygons. Mesh 144 may optionally form squares.
  • the meshes of the mesh 144 can surround channels 146 in which the first fluid circulates. These channels 146 can be separated from each other by the mesh 144.
  • the network includes a partition 148 which marks the separation between the first and the second fluid. The heat exchange takes place through this partition 148. It also forms the structure of the matrix 130. Inside, the channels 146 are blocked by successive fins (138; 140), preferably by several series successive fins.
  • the figure 6 shows an enlargement of a channel 146 representative of those shown in figure 5 .
  • the fins (138; 140) are located on the partition 148. They can connect the opposite faces thereof.
  • the fins (138; 140) can form crosses, for example by joining two coplanar and secant fins.
  • the set of fins (138; 140) can form a row of successive crosses.
  • the various crosses are pivoted relative to each other to optimize heat exchange while limiting pressure drops. For example, each cross is rotated 22.5° relative to its upstream cross. A pattern of four regularly rotated crosses can be repeated.
  • the crosses form helical passages 136 inside the channels 146, for example four helical passages 136 wrapped around each other. 146 channels can be straight or twisted.
  • the figure 7 is partial section along axis 7-7 drawn on the figure 5 .
  • Three channels 146 are shown, as are four mesh portions 144 in which circulates the second fluid; for example oil.
  • the front fins 138 are visible over their entire lengths while the rear fins 140 are only partially visible since they remain in section.
  • the following crosses are also partially represented via their hubs 150 crossing their fins.
  • the crosses are formed in planes. These planes are parallel to each other, and inclined with respect to the secondary flow 120; either inclined with respect to the flow of the first fluid.
  • the angle of inclination ⁇ between the planes 152 of fins and the general flow of the first fluid can be between 30° and 60°.
  • the angle of inclination ⁇ may optionally be equal to 45°. From this it follows that the passages 146 comprise sections inclined with respect to the general direction of the flow of the first fluid through the matrix 130. This arrangement induces the first fluid to change section as it circulates, and to better cool the staggered fins.
  • the figure 8 shows a diagram of a method of making a heat exchanger matrix.
  • the matrix produced may correspond to those described in relation to the figures 2 to 7 .
  • the printing direction can be inclined relative to the tubes by an angle between 30° and 50°. If necessary, the direction of printing can be substantially parallel to the channels, or inclined by less than 10°, or by less than 4°.
  • Additive manufacturing can be done from powder, possibly titanium or aluminum.
  • the thickness of the layers can be between 20 ⁇ m and 50 ⁇ m, which makes it possible to achieve a fin thickness of the order of 0.35 mm, and partitions of 0.60 mm.
  • the collectors can be made of mechanically welded sheets, then welded to the ends of the matrix to form a collector.
  • the material of the matrix can show a stack of layers. These layers can be parallel.
  • the layers can show crystallographic variations at their interfaces.
  • each fin is inclined with respect to the layers, in particular to the layers forming it.
  • the figure 9 shows a 300 aircraft seen from above. It can be a jet plane.
  • the aircraft 300 may have a fuselage 360, notably defining the main body. It can comprise two side wings 362, in particular connected by the fuselage 360. The side wings 362 can be arranged between the cockpit 366 and the tail 364 of the aircraft 300.
  • Each of the side wings 362 can receive one or more turbomachines 2, in particular turbojet engines, making it possible to propel the aircraft 300 in order to generate a lift phenomenon in combination with the side wings 362.
  • At least one, or each, or more turbomachines 2 can be identical or similar to that presented in connection with the figure 1 .
  • the aircraft 300 comprises at least one matrix, in particular a matrix 30 of heat exchanger 24.
  • one or more matrices 30 of heat exchanger 24 may/may be housed in the fuselage 360.
  • one or more heat exchanger dies 24 can be housed in one or more side wings 362, and/or in one or more or in each turbomachine 2.
  • At least one, or more, or each heat exchanger die may be the same or similar to one or more of the figures 2 to 7 , for example according to the first or the second embodiment of the invention.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Geometry (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Claims (15)

  1. Die Matrix (30; 130) eines Wärmetauschers (24) zwischen einem ersten Fluid und einem zweiten Fluid, nämlich eine Matrix (30; 130) eines Wärmetauschers für eine Turbomaschine (2), wobei die Matrix (30; 130) aus Folgendes besteht:
    einem Rohr für die Strömung des ersten Fluids;
    einem Netzwerk, das sich in dem Rohr fortsetzt und durch das das zweite Fluid strömt;
    das Netzwerk mindestens zwei aufeinanderfolgende Lamellen (38; 40, 138; 140) trägt, die von der Strömungsrichtung des ersten Fluids abhängen, insbesondere die Kühllamellen;
    die aufeinanderfolgenden Lamellen (38; 40, 138; 140) sind eben und erstrecken sich im ersten Fluid in Richtung der Hauptrichtungen, die zueinander um eine Achse geneigt sind, die parallel zur Strömungsrichtung (20; 120) des ersten Fluids angeordnet ist, dadurch gekennzeichnet, dass jede Lamelle mit zwei gegenüberliegenden Enden versehen ist, die mit dem Netzwerk verbunden sind.
  2. Die Matrix (30; 130) nach Anspruch 1, dadurch gekennzeichnet, dass die Hauptrichtungen der aufeinanderfolgenden Lamellen (38; 40; 138; 140) relativ zueinander um mindestens 10° oder mindestens 45° geneigt sind.
  3. Die Matrix (30; 130) nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die aufeinanderfolgenden Lamellen (38; 40; 138; 140) aufeinanderfolgende Kreuzungen gemäß der Strömungsrichtung des ersten Fluids bilden, wobei die Kreuzungen relativ zueinander schwenkbar sind.
  4. Die Matrix (30; 130) nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die aufeinanderfolgenden Lamellen (38; 40; 138; 140) sich von einem Bereich des Netzwerks aus fortsetzen und in Bezug auf eine Ebene senkrecht zum Strömungsbereich des ersten Fluids vorstehen, wobei die aufeinanderfolgenden Lamellen in einem Abstand von diesem Bereich des Netzwerks enden.
  5. Die Matrix (30; 130) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die aufeinanderfolgenden Lamellen (138; 140) ineinander übergehen.
  6. Die Matrix (30) nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass sie mit einem Einlassbereich (41) und einem Auslassbereich (43) für das erste Fluid versehen ist, wobei der Einlassbereich (41) und der Auslassbereich (43) durch eine Leitung verbunden sind und die Matrix mit einer äußeren Schicht (45) versehen ist, in der der Einlassbereich (41) und der Auslassbereich (43) angeordnet sind.
  7. Die Matrix (30) nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Matrix aus mehreren Röhren (34) besteht, die parallel angeordnet sein können und/oder Röhren (34) mit ellipsen-, tropfen- oder rautenförmigen Profilen haben.
  8. Die Matrix (130) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Matrix ein Netz (144) aufweist.
  9. Die Matrix (130) nach Anspruch 8, dadurch gekennzeichnet, dass das Netz (144) in der Strömungsrichtung des ersten Fluids profiliert ist und/oder das Netz (144) Kanäle (146) für die Strömung des ersten Fluids definiert, wobei die Kanäle im Schnitt vier Winkel aufweisen.
  10. Eine Turbomaschine (2), nämlich ein Turbotriebwerk, bestehend aus Lagern (22), einem Getriebe (17), das ein Gebläse (16) antreibt, und einem Wärmetauscher (24), der mit einer Matrix (30; 130) versehen ist, dadurch gekennzeichnet, dass die Matrix (30; 130) einem der Ansprüche 1 bis 9 entspricht, wobei der Wärmetauscher ein Luft-Öl-Wärmetauscher ist, wobei die Luft das erste Fluids ist und das Öl das zweite Fluid ist.
  11. Eine Turbomaschine (2) nach Anspruch 10, dadurch gekennzeichnet, dass das Öl ein Schmier- und/oder Kühlöl ist und/oder die Turbomaschine (2) einen Lufteinlassstutzen (16) aufweist.
  12. Ein Verfahren zur Bildung einer Matrix (30; 130) für einen Wärmetauscher (24) zwischen einem ersten Fluid und einem zweiten Fluid, wobei die Matrix (30; 130) aus folgenden Teilen besteht: einer Leitung für den Durchfluss des ersten Fluids; einem Netzwerk, das sich in der Leitung fortsetzt und durch das das zweite Fluid fließt; wobei das Verfahren aus den folgenden Schritten besteht:
    (a) Auslegung (200) des Wärmetauschers (24) und der Matrix(30; 130), mit der er versehen ist;
    (b) Herstellung (202) der Matrix durch zusätzliche Herstellung mittels einer Direktdrucktechnik;
    dadurch gekennzeichnet, dass der Schritt (b) der Herstellung in der Fertigung von Lamellen (38; 40; 138; 140) besteht, die sich in Richtung der Hauptrichtungen, die in Bezug auf die Druckrichtung geneigt sind, fortsetzen, wobei die Matrix (30; 130) nach einem der Ansprüche 1 bis 11 hergestellt wird.
  13. Ein Verfahren nach Anspruch 12, dadurch gekennzeichnet, dass die Lamellen (38; 40, 138; 140) auf Ebenen (152) angeordnet sind, die in Bezug auf die Druckrichtung um einen Winkel β zwischen 20° und 60° geneigt sind, der zwischen 30° und 50° liegen kann.
  14. Ein Verfahren nach einem der Ansprüche 12 bis 13, dadurch gekennzeichnet, dass Schritt (b) der Herstellung (202) die Fertigung von Röhren (34) umfasst, die in Bezug auf die Druckrichtung in einem Winkel zwischen 20° und 60°, der zwischen 30° und 50° liegen kann, geneigt sind.
  15. Ein Verfahren nach einem der Ansprüche 12 bis 14, dadurch gekennzeichnet, dass Schritt (b) der Herstellung darin besteht, Kanäle (144) im Wesentlichen parallel zur Druckrichtung herzustellen.
EP17772077.8A 2016-10-03 2017-09-29 Matrix für einen luft-öl-wärmetauscher eines strahltriebwerks Active EP3519753B1 (de)

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BE1024621B1 (fr) 2018-05-24
CN114577039B (zh) 2024-07-09
US20190170450A1 (en) 2019-06-06
EP3519753A1 (de) 2019-08-07
WO2018065304A1 (fr) 2018-04-12
US11125511B2 (en) 2021-09-21
CN114577039A (zh) 2022-06-03
BE1024621A1 (fr) 2018-04-26
CN110168299A (zh) 2019-08-23
US20220074678A1 (en) 2022-03-10

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