EP2199725B1 - Structure d'un surface avec noyau de refroidissement par impact - Google Patents

Structure d'un surface avec noyau de refroidissement par impact Download PDF

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Publication number
EP2199725B1
EP2199725B1 EP08021833A EP08021833A EP2199725B1 EP 2199725 B1 EP2199725 B1 EP 2199725B1 EP 08021833 A EP08021833 A EP 08021833A EP 08021833 A EP08021833 A EP 08021833A EP 2199725 B1 EP2199725 B1 EP 2199725B1
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EP
European Patent Office
Prior art keywords
impingement
webs
composite
layers
perforated sheet
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.)
Not-in-force
Application number
EP08021833A
Other languages
German (de)
English (en)
Other versions
EP2199725A1 (fr
Inventor
Andreas Heselhaus
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP08021833A priority Critical patent/EP2199725B1/fr
Priority to AT08021833T priority patent/ATE528606T1/de
Priority to JP2009283250A priority patent/JP5511352B2/ja
Priority to RU2009146588/06A priority patent/RU2518773C2/ru
Priority to CN200910253488.8A priority patent/CN101787904B/zh
Publication of EP2199725A1 publication Critical patent/EP2199725A1/fr
Application granted granted Critical
Publication of EP2199725B1 publication Critical patent/EP2199725B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B22F7/064—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts using an intermediate powder layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling
    • F01D5/183—Blade walls being porous
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling
    • F01D5/184—Blade walls being made of perforated sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
    • C21C5/00—Manufacture of carbon-steel, e.g. plain mild steel, medium carbon steel or cast steel or stainless steel
    • C21C5/28—Manufacture of steel in the converter
    • C21C5/42—Constructional features of converters
    • C21C5/46—Details or accessories
    • C21C5/4646—Cooling arrangements
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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
    • F28D2021/0077—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for tempering, e.g. with cooling or heating circuits for temperature control of elements
    • F28D2021/0078—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for tempering, e.g. with cooling or heating circuits for temperature control of elements in the form of cooling walls

Definitions

  • the invention relates to a multi-impingement composite for cooling a wall, a wall with the multi-impingement composite and a method for producing the multi-impingement composite.
  • a generic composite is off GB-A-2 061 482 known.
  • the hot gas leading part has a wall at which it is in contact with the hot gas on one side in contact and is cooled on its other side with the cooling air.
  • a heat flow is transported away from the wall, so that the wall at its side facing the hot gas has a contact temperature which is below the hot gas temperature.
  • the porous structure abuts against the wall, so that heat is transferred from the wall into a porous structure by heat conduction and heat radiation.
  • the porous structure in turn gives in her the volume of heat to the cooling air, with the heat from the porous structure can be removed.
  • the structure needs to have only a relatively small volume on these walls in order to transmit a desired heat flow from the wall to the cooling air can.
  • the wall may have a plurality of film cooling holes through which the cooling air is directed through the wall into the hot gas flow, thereby forming a film of cooling air on the hot gas side surface of the wall.
  • the cooling air flows out of the porous structure into the hot gas flow, so that a uniform flow through the porous structure is achieved perpendicular to the wall.
  • the film cooling can approach their ideal borderline case, the effusion cooling.
  • an optimally heat-insulating film of cooling air adjusts itself to the hot gas-side surface of the wall at the same time.
  • the porous structure may for example be made of a metal foam, which has only a random structure with a stochastically distributed pore size due to its conventional manufacturing process.
  • the metal foam is inexpensive to manufacture, but has significant disadvantages.
  • the metal foam may be partially closed, which thereby have too small a width, so that there is a risk of clogging of these pores.
  • the metal foam has sharp edges in its interior, whereby an increased pressure loss can occur when flowing through the metal foam with the cooling air.
  • the metal foam has a plurality of pores in its interior delimiting webs whose stochastically constant diameter is detrimental to the heat conduction.
  • a designed porous structure which in principle can have any optimal geometry.
  • the designed porous structure can be produced, for example, by the production process "selective laser melting” or “selective sintering".
  • these production methods have the disadvantage that they can be used to produce the designed porous structure only up to a maximum of 6 PPI (pores per inch) and a minimum web thickness of 0.6 to 1 mm.
  • these design structures produced in this way are not suitable for the previously mentioned, flat and to be cooled walls, as this PPI rates of 40 to 50 PPI would be required.
  • the "selective laser melting” is very time consuming and costly.
  • a designed porous structure for cooling example of Schaufelend outfitn, ring segments on blades, Transitionswanditch and burner walls, such. Z. can still be produced, still significant disadvantages.
  • a designed porous structure 101 is shown.
  • the designed porous structure 101 has a plurality of pores 102 formed by ridges 103 that converge at nodes 104.
  • the high heat transfer of the designed porous structure 101 is due to the multiplicity of repetitive stagnation point flows as it flows through the designed porous structure 101 with the cooling air. It is characterized by the one of the pores 102, which is the shape of in Fig. 4 has drawn pyramid, the cooling air flow accelerates, which bounces on one of the webs 103 or one of the nodes 104, wherein a high local heat transfer is formed. From there, the flow of cooling air through the next opening is accelerated again to bounce on the next node 104 or webs 103.
  • Object of the invention is to provide a multi-impingement composite for cooling a wall, a wall with the multi-impingement composite and a method for producing the multi-impingement composite, wherein the flow through the multi-impingement composite a high Number of impingement cooling flows can be generated, which with the multi-impingement composite, the wall is effectively cooled.
  • the multi-impingement composite according to the invention can be contacted with the surface of a wall to be cooled and thermally conductive and has a plurality of pinhole layers with a plurality of pinhole formed, distributed over the surface of the pinhole layers arranged through holes and a plurality of web layers, with the pinhole layers are arranged alternately stacked and each having a plurality of webs which are arranged distributed over the surface of the pinhole layers and bridge each of these, each web of a web layer is arranged in alignment with one of the webs of the other web layers and each through hole of the one Pinhole layer is arranged offset to the through holes of the adjacent pinhole layers, so that when the multi-impingement composite is pressurized on its one flat side with the cooling fluid, the cooling fluid through the fürgangslöc flows forth and then between the jetties and the apertured diaphragm layers settled by flooding, whereby the heat flow derived in the webs of the wall with the cooling fluid can be discharged.
  • the multi-impingement composite thus has a plurality of layers on the pinhole layers, which are arranged one above the other and have mutually staggered through holes. Through the through holes, the cooling fluid is cascaded in an impingement cooling flow on the respective underlying level can be brought.
  • the last (hot) or the first (cold) plane represents the wall, which can be significantly thicker than the impact cooling planes.
  • the planes are interconnected by the webs, which are formed as connecting elements of the pinhole layers.
  • the webs conduct heat from the wall to be cooled to the other levels, so that heat can also be transferred there in the impingement cooling flows. For this purpose, the webs are aligned on top of each other.
  • the webs each have the largest possible cross-sectional area, so that the heat transfer rate along the webs is high.
  • the cross-sectional area of the webs are only selected to be so large that the pressure losses in the flow of cooling fluid caused by the webs and the concomitant impairment of the heat transfers in the impact cooling flows are not excessively high.
  • the orders of magnitude of the cross-sectional areas of the webs also result from the distance between the through holes.
  • the multi-impingement composite With the distance to the hot, to be cooled wall, the proportion of the heat flow decreases, which is absorbed by the cooling medium. Thus, in far from the wall remote impact cooling layers, the proportion of the heat flow is small, which is absorbed by the cooling medium. Thereby, it is sufficient to limit the thickness of the multi-impingement composite to a maximum necessary extent, so that the multi-impingement composite has a sufficient number of pinhole layers and land layers designed for a predetermined heat transfer line and for a given pressure loss.
  • the Geometry of the multi-impingement composite can be optimized for overall heat transfer and overall pressure loss.
  • the distances between the lands and the distances between the through holes may be from less than 1 mm to several centimeters.
  • the multi-impingement composite is formed as an extreme case of the designed porous structure, wherein the multi-impingement composite has a high geometric patterning.
  • the area of stagnation point flow is limited to a very small cross-section formed by the area of the structural elements struck by the cooling fluid. This necessitates the aforementioned concentration of as many stagnation points per volume as possible, thereby requiring a high PPI rate of the porous structure.
  • the high stagnation point heat transfer area extends to the entire gap between the limiting land layers. As a result, the distance between the lands and the through holes need not be as small as would be necessary with a designed 40 to 50 PPI porous structure.
  • the impingement of the laterally propagating impingement cooling fluid on the webs results in a turbulence which ensures a similarly high heat transfer at the webs and further downstream impact surface, as in the stagnation point region itself.
  • the entire inner surface of the multi-impingement composite becomes high heat transfer, although the distance between the lands and the through holes may be much greater than 40 to 50 PPI.
  • the longitudinal directions of the webs extend perpendicular to the pinhole layers. Furthermore, the webs are in a rectangular grid evenly over the surface arranged the Lochblendenechichten distributed.
  • the through holes are each equidistant from four immediately adjacent lands, and the gap formed between the four lands has either one of the through holes in either one orifice plate or in the other pinhole layer such that the through holes are in gap.
  • the webs have a lancet-shaped cross section with two opposite blunt edges and two opposite sharp edges.
  • the through-holes of the adjacent apertured diaphragm layer through which the cooling fluid flows in the gap formed between the four webs when the cooling fluid pressure is applied to the multi-impingement composite on one flat side thereof.
  • the through-holes of the adjacent pinhole layer through which the cooling fluid flows into the gap formed between the four lands when the multi-impingement composite impinges on its one flat side with the cooling fluid pressure is.
  • the pinhole plates are preferably rounded or touched. This reduces pressure losses in the multi-impingement composite, which can reduce the pressure of the cooling fluid to be applied to the multi-impingement composite. By further rounding the transitions between the pinhole plates and the webs, the stresses in the pinhole plates and the webs would advantageously distributed such that excessive voltage spikes are prevented.
  • the wall of the invention has the multi-impingement composite, which is contacted with the surface of the wall surface and heat-conducting.
  • the multi-impingement composite preferably rests against one of the web layers on the wall, and the wall preferably has a plurality of through-holes, so that the wall is formed as one of the pinhole layers.
  • the distribution density of the through holes in the wall may advantageously be chosen to be the same as the distribution density of the through holes in the pinhole layers, so that an optimal, directed perpendicular to the wall flow is made possible.
  • the Effusionsksselungscou can be optimally used in closely spaced through holes in the wall.
  • the hole density in the wall can also be different from that in the pinhole plates.
  • the method according to the invention for producing the multi-impingement composite comprises the step of printing individual layers of the multi-impingement composite together in a screen printing process, wherein a screen mask is produced for each of two apertured diaphragm layers and a web layer, through which a paste is pressed.
  • the paste preferably comprises metal powder and binder.
  • the multi-impingement composite is preferably sintered.
  • the thickness of the pinhole plates preferably has the same order of magnitude as the thickness of the web layers.
  • the screen mask is made photochemically from a metal foil.
  • the paste consisting of metal powder and binder is pressed for each layer through the pores of the screen mask, which is later preferably sintered as a whole. If the process parameters are known, such as formulation, drying time and shrinkage, the process can run cost-effectively in mass production.
  • the other method of making the multi-impingement composite according to the invention comprises the steps of: prefabricating blocks of the multi-impingement composite from layers of constant cross-section; Pre-drying and stacking the blocks. It is preferred that the multi-impingement composite is sintered.
  • the thickness of the pinhole plates preferably has the same order of magnitude as the thickness of the web layers. If the blocks of the multi-impingement composite are prefabricated, they are pre-dried and precisely stacked and then joined together in the sintering process.
  • the basis for high manufacturing accuracy in the production of the multi-impingement composite is the high-precision production of the molds for the blocks.
  • the molds are made by a photochemical process that is applied to individual layers of the mold made from metal foils.
  • An alternative method of making the multi-impingement composite comprises the steps of: forming the apertured plate layers and the fin layers of thin metal foils; Stacking the metal foils to form the multi-impingement composite; Connecting the metal foils averages "transient liquid phase bonding".
  • the metal foils are stacked directly and bonded by means of transient liquid face bonding, wherein the metal foils were photochemically shaped into individual layers of the positive of the multi-impingement composite to be produced.
  • the screen printing method can be advantageously used. For larger distances between the webs, however, there is a risk that the overhanging printed film may tear.
  • the method of making the multi-impingement composite with prefabricated blocks of pre-dried sintered / binder material may be used for a pitch of lands and through-holes that is 10mm and larger.
  • the "transient liquid face bonding" of the individual metal foils can be used with a grid pitch greater than 10 mm.
  • the multi-impingement composite 1 has a plurality of web layers 6, each between two adjacent
  • Aperture layers 2 are arranged so that the multi-impingement composite 1 has a formed from the pinhole layers 2 and the web layers 4 sandwich structure.
  • the web layers 6 are formed from a plurality of webs 7, which are also arranged like a raster similar to the through holes 3 and are perpendicular to the pinhole layers 2 with their longitudinal directions. As a result, with each web 7, the distance between two adjacent apertured diaphragm layers 2 is bridged so that heat can be transmitted from one apertured diaphragm layer 2 via the web 7 to the other apertured diaphragm layer 2.
  • a gap 8 is formed, into which either the inlet side 4 of one of the through holes 3 or the outlet side 5 of one of the through holes 3 opens.
  • the through holes 3 are arranged on a gap.
  • the webs 7 of a web layer 6 are each arranged in alignment with their immediate neighbors of the other web layers, wherein the webs 7 in the first embodiment according to the invention of the multi-impingement composite according to Fig. 1 each have a circular cross-section 9.
  • the webs 7 according to the second embodiment of the multi-impingement composite according to the invention have Fig. 2 a lancet-shaped cross-section, which is formed by two opposite acute edges 11 and two opposite obtuse edges 12, wherein the sharp edges 11 and the blunt edges 12 are arranged alternately when the boundary of the lancet-shaped cross section 10.
  • a flat with a wall to be cooled and thermally conductive contactable flat side 17 of the multi-impingement composite 1 is provided. Facing away from this flat side 17, a flat side 16 which can be pressurized with a cooling medium is provided on the multi-impingement composite 1.
  • the cooling medium flows through the through holes 3 and enters at the exit side 5 in one of the intermediate spaces 8 with a main flow 13 a. Characterized in that the diameter of the through holes 3 is smaller than the width of the intermediate spaces 8, a turbulence 14 of the cooling fluid sets in the gap 8 a.
  • a transverse flow 14 sets in, which flows from an impact point 16 of the main flow 13 on the aperture diaphragm layer 2 to the inlet openings 4 of the through holes 3 arranged offset in the next plane.
  • the cooling fluid then exits at the inlet side 4 of the through hole 3 from the intermediate space 8 as the main flow 13 again and passes through the outlet side 5 of the through hole 3 to the underlying gap 8.
  • Opposite to the main flow 13 is formed by the webs 7 from the wall transmit a heat flow 15 a.
  • the heat flow 15 is seen in the direction of the main flow 13 seen from space 8 to space 8 by convective heat transfer to the cooling fluid, so that with the cooling fluid, the wall is cooled, also the heat flow, which flows into each pinhole layer 2, through the perpendicular
  • the main diaphragm 13 impinging on the pinhole diaphragm layer 2 is partially absorbed by the cooling fluid.

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  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Claims (12)

  1. Composite multi-impingement pour le refroidissement d'une paroi au moyen d'un fluide de refroidissement, dans lequel le composite multi-impingement peut être mis en contact (17) suivant une surface et d'une manière conductrice de la chaleur avec la surface de la paroi ainsi qui comprend une pluralité de trous (3) traversants constitués sous la forme de diaphragmes à trou et répartis sur la surfaces des couches (2) de diaphragmes à trou et une pluralité de couches (6) de parties pleines, qui sont empilées en alternance avec les couches (2) de diaphragme à trou et ont respectivement une pluralité de parties pleines (7), qui sont réparties sur la surface des couches (2) de diaphragmes à trou et les enjambent respectivement, chaque partie pleine (7) de l'une des couches (6) de parties pleines étant disposée en alignement avec respectivement l'une des parties pleines (7) de l'autre couche (7) de parties pleines et chaque trou (3) traversant de l'une des couches (2) de diaphragmes à trou étant décalé par rapport aux autres trous (3) traversants des couches (3) voisines de diaphragmes à trou, de manière à ce que, lorsque le composite (1) multi-impingement est soumis à la pression du fluide de refroidissement sur l'une de ses faces (16) planes, le fluide de refroidissement passe dans les trous (3) traversants et s'écoule dans les espaces (8) intermédiaires entre les parties pleines (7) et les couches (2) de diaphragmes à trou, de sorte que le flux (15) calorifique, évacué de la paroi dans les parties pleines (7), peut être évacué par le fluide de refroidissement, les directions longitudinales des parties pleines (7) s'étendant perpendiculairement aux couches (2) de diaphragmes à trou et les parties pleines (7) étant réparties uniformément suivant une trame rectangulaire sur la surface des couches (2) de diaphragmes à trou et les trous (3) traversants étant disposés en étant respectivement équidistants de quatre parties pleines (7) directement voisines et l'espace (8) intermédiaire formé entre les quatre parties pleines (7) a l'un des trous (3) traversants dans l'une des couches (2) de diaphragmes à trou ou dans l'autre couche (2) de diaphragmes à trou, de sorte que les trous (3) traversants sont sur des lacunes,
    caractérisé en ce que
    les parties pleines (7) ont une section (10) transversale en forme de lancettes ayant deux bords (12) opposés non pointus et deux bords (11) opposés pointus.
  2. Composite multi-impingement suivant la revendication 1, dans lequel les trous (3) traversants de la couche (2) de diaphragmes à trou, dans laquelle le fluide de refroidissement sort dans l'espace (8) intermédiaire formé entre les quatre parties pleines (7), lorsque le composite (1) multi-impingement est soumis à la pression du fluide de refroidissement sur l'une de ses faces (16) planes, se trouvent sur des lignes imaginaires croisant les bords (11) pointus.
  3. Composite multi-impingement suivant la revendication 1 ou 2,
    dans lequel les trous (3) traversants de la couche (2) de diaphragmes à trou, dans laquelle le fluide de refroidissement sort dans l'espace (8) intermédiaire formé entre les quatre parties pleines (7), lorsque le composite (1) multi-impingement est soumis à la pression du fluide de refroidissement sur l'une de ses faces (16) planes, se trouvent sur des lignes imaginaires croisant les bords (12) qui ne sont pas pointus.
  4. Composite multi-impingement suivant l'une des revendications 1 à 3,
    dans lequel les plaques (2) de diaphragmes à trou sont arrondies sur les trous (3) traversants.
  5. Paroi ayant un composite multi-impingement suivant l'une des revendications 1 à 4,
    dans laquelle le composite (1) multi-impingement est en contact (17) suivant une surface et d'une manière conductrice de l'électricité avec la surface de la paroi.
  6. Paroi suivant la revendication 5,
    dans laquelle le composite multi-impingement s'applique à la paroi par l'une des couches (6) de parties pleines et la paroi a une pluralité de trous (3) traversants, de sorte que la paroi est formée en tant que l'une des couches (2) de diaphragmes à trou.
  7. Procédé de fabrication d'un composite (1) multi-impingement suivant l'une des revendications 1 à 4, comprenant le stade :
    on imprime les unes sur les autres diverses couches du composite multi-impingement par un procédé de sérigraphie, dans lequel on produit, respectivement pour deux couches (2) de diaphragmes à trou et pour une couche (7) de parties pleines, un masque de sérigraphie, à travers lequel une pâte est refoulée.
  8. Procédé suivant la revendication 7, dans lequel la pâte comporte de la poudre métallique et du liant.
  9. Procédé suivant la revendication 7 ou 8, dans lequel on produit photochimiquement le masque de sérigraphie en un feuillard métallique.
  10. Procédé de fabrication d'un composite (1) multi-impingement suivant l'une des revendications 1 à 4, comprenant les stades :
    - on prépare à l'avance des blocs du composite (1) multi-impingement composés de couches de section transversale constante ;
    - on sèche à l'avance et on empile les blocs les uns sur les autres.
  11. Procédé suivant l'une des revendications 7 à 10, dans lequel on fritte le composite (1) multi-impingement.
  12. Procédé suivant l'une des revendications 7 à 11, dans lequel l'épaisseur des plaques (2) de diaphragmes à trou est du même ordre de grandeur que l'épaisseur des couches (7) de parties pleines.
EP08021833A 2008-12-16 2008-12-16 Structure d'un surface avec noyau de refroidissement par impact Not-in-force EP2199725B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP08021833A EP2199725B1 (fr) 2008-12-16 2008-12-16 Structure d'un surface avec noyau de refroidissement par impact
AT08021833T ATE528606T1 (de) 2008-12-16 2008-12-16 Multi-impingement-verbund zum kühlen einer wand
JP2009283250A JP5511352B2 (ja) 2008-12-16 2009-12-14 壁を冷却するための多重インピンジメント複合体
RU2009146588/06A RU2518773C2 (ru) 2008-12-16 2009-12-15 Многоотражательный многослойный комплекс для охлаждения стенки и способ изготовления такого многоотражательного многослойного комплекса (варианты)
CN200910253488.8A CN101787904B (zh) 2008-12-16 2009-12-16 用于冷却壁体的多冲击复合结构

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08021833A EP2199725B1 (fr) 2008-12-16 2008-12-16 Structure d'un surface avec noyau de refroidissement par impact

Publications (2)

Publication Number Publication Date
EP2199725A1 EP2199725A1 (fr) 2010-06-23
EP2199725B1 true EP2199725B1 (fr) 2011-10-12

Family

ID=40600134

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08021833A Not-in-force EP2199725B1 (fr) 2008-12-16 2008-12-16 Structure d'un surface avec noyau de refroidissement par impact

Country Status (5)

Country Link
EP (1) EP2199725B1 (fr)
JP (1) JP5511352B2 (fr)
CN (1) CN101787904B (fr)
AT (1) ATE528606T1 (fr)
RU (1) RU2518773C2 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10156359B2 (en) 2012-12-28 2018-12-18 United Technologies Corporation Gas turbine engine component having vascular engineered lattice structure
US10018052B2 (en) 2012-12-28 2018-07-10 United Technologies Corporation Gas turbine engine component having engineered vascular structure
GB201403404D0 (en) 2014-02-27 2014-04-16 Rolls Royce Plc A combustion chamber wall and a method of manufacturing a combustion chamber wall
CN105222158B (zh) * 2014-06-30 2018-04-13 中国航发商用航空发动机有限责任公司 浮动瓦块以及燃烧室火焰筒
US10094287B2 (en) 2015-02-10 2018-10-09 United Technologies Corporation Gas turbine engine component with vascular cooling scheme
EP3170980B1 (fr) * 2015-11-23 2021-05-05 Raytheon Technologies Corporation Composants pour moteur à turbine à gaz avec structure de refroidissement en treillis et procédé de production associé
US10077664B2 (en) 2015-12-07 2018-09-18 United Technologies Corporation Gas turbine engine component having engineered vascular structure
US10221694B2 (en) 2016-02-17 2019-03-05 United Technologies Corporation Gas turbine engine component having vascular engineered lattice structure
JP6717662B2 (ja) * 2016-05-20 2020-07-01 株式会社Ihi ラティス構造
CN109642472B (zh) * 2016-08-30 2021-07-06 西门子股份公司 用于燃气轮机的冲击冷却特征
WO2018186891A1 (fr) 2017-04-07 2018-10-11 General Electric Company Ensemble de refroidissement pour ensemble turbine
US10774653B2 (en) 2018-12-11 2020-09-15 Raytheon Technologies Corporation Composite gas turbine engine component with lattice structure

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US3900629A (en) * 1973-09-14 1975-08-19 Bendix Corp Porous laminate and method of manufacture
GB2049152B (en) * 1979-05-01 1983-05-18 Rolls Royce Perforate laminated material
US4296606A (en) * 1979-10-17 1981-10-27 General Motors Corporation Porous laminated material
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
US5145001A (en) * 1989-07-24 1992-09-08 Creare Inc. High heat flux compact heat exchanger having a permeable heat transfer element
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RU2168039C2 (ru) * 1996-07-05 2001-05-27 Общество с ограниченной ответственностью "Научно-исследовательский институт природных газов и газовых технологий - ВНИИГАЗ" Двигатель внутреннего сгорания с уменьшенным теплоотводом и способ его изготовления
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Also Published As

Publication number Publication date
EP2199725A1 (fr) 2010-06-23
RU2518773C2 (ru) 2014-06-10
RU2009146588A (ru) 2011-06-20
JP2010144722A (ja) 2010-07-01
JP5511352B2 (ja) 2014-06-04
CN101787904A (zh) 2010-07-28
CN101787904B (zh) 2016-06-08
ATE528606T1 (de) 2011-10-15

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