EP2554904A2 - Dispositif de chambre de combustion ou dispositif de chambre de poussée - Google Patents

Dispositif de chambre de combustion ou dispositif de chambre de poussée Download PDF

Info

Publication number
EP2554904A2
EP2554904A2 EP12179345A EP12179345A EP2554904A2 EP 2554904 A2 EP2554904 A2 EP 2554904A2 EP 12179345 A EP12179345 A EP 12179345A EP 12179345 A EP12179345 A EP 12179345A EP 2554904 A2 EP2554904 A2 EP 2554904A2
Authority
EP
European Patent Office
Prior art keywords
wall
combustion chamber
chamber device
wall device
fibers
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.)
Granted
Application number
EP12179345A
Other languages
German (de)
English (en)
Other versions
EP2554904B1 (fr
EP2554904A3 (fr
Inventor
Hermann Hald
Markus Ortelt
Dirk Greuel
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP2554904A2 publication Critical patent/EP2554904A2/fr
Publication of EP2554904A3 publication Critical patent/EP2554904A3/fr
Application granted granted Critical
Publication of EP2554904B1 publication Critical patent/EP2554904B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • 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
    • F23M5/08—Cooling thereof; Tube walls
    • 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
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining

Definitions

  • the invention relates to a combustion chamber device or Schubschvoriques.
  • a combustion chamber comprising an outer jacket and an inner jacket, which defines a combustion chamber and which is fluid-permeable for effusion cooling or transpiration cooling, wherein the inner jacket comprises a plurality of successive disc elements along an axial axis.
  • a fuel is burned with an oxidizer and combustion gases can create a boost.
  • a combustion chamber device is a specific example of a thrust chamber device.
  • a thrust can be generated via gases, even if no combustion takes place, for example by heating a gas in a manner other than nuclear.
  • the invention has for its object to provide a combustion chamber device with high structural stability and high temperature resistance.
  • a first wall means which defines a combustion chamber or a pusher space with an inner side
  • a second wall means is provided, which faces with the inside of an outer side of the first wall means is provided
  • the first Wall device is made of a ceramic composite material
  • a cooling channel device for cooling the first wall device with a cooling fluid which comprises at least one cooling channel, which arranged on the first wall means and / or the second wall means and / or between the first wall means and the second wall means or is formed, is provided, wherein in the first wall means fibers of high thermal conductivity are arranged, which are arranged in the heat transport direction away from the inside and which have a thermal conductivity of at least 100 W / mK.
  • a ceramic composite material such as a carbide-ceramic material or oxide-ceramic material basically has a high temperature resistance.
  • the material has a relatively low coefficient of thermal expansion, in particular in comparison to a metallic material.
  • the first wall device is correspondingly thick, then it is correspondingly structurally stable and it is possible to achieve a high temperature at a hot gas side. As a result, a high temperature gradient can arise via the first wall device. However, this can lead to high thermal stresses with the corresponding material problems.
  • the fibers of high thermal conductivity have a thermal conductivity (in particular integral thermal conductivity) of at least 100 W / mK, preferably at least 300 W / mk, and in particular up to more than 600 W / mK. This allows effective heat dissipation to be achieved.
  • the fibers of high thermal conductivity are arranged protected in the matrix of the ceramic composite.
  • fiber ends of fibers of high thermal conductivity terminate at or near the inside of the first wall device. This allows effective heat conduction paths along the corresponding fibers provide. Furthermore, for example, the inside can then be sanded off well and a homogeneous, rough surface can be obtained, which in turn is a good carrier for a coating.
  • fibers of high thermal conductivity are guided from the inside of the first wall device to the at least one channel. This effectively dissipates heat into a channel in which a cooling fluid flows.
  • fiber ends of fibers of high thermal conductivity terminate at a flow space or in the vicinity of a flow space of the at least one channel. This provides an effective heat conduction path across a fiber.
  • the at least one channel has an extension direction which is at least approximately parallel to an axial axis of the first wall device. It is advantageous if a cooling fluid is guided against a main flow direction in the combustion chamber or pusher chamber. As a result, effective cooling in countercurrent principle can be achieved. Furthermore, for example, a cooling fluid, which is then used as fuel, can be preheated.
  • fibers of high thermal conductivity are aligned at least approximately in the radial direction with respect to an axial axis of the first wall device.
  • first wall means has a uniform thickness, it is possible to provide a heat conduction path of minimized length, and thereby heat can be effectively dissipated.
  • Not all fibers have to be aligned radially.
  • the majority of the fibers (for example, more than 70%) are aligned at least approximately radially.
  • the first wall device is designed in particular as an inner liner.
  • the second wall device surrounds the first wall device.
  • the second wall device is designed in particular as an outer liner.
  • a plurality of cooling channels which are spaced in a circumferential direction, are formed on the first wall device in the region of the outside.
  • the cooling channels are thereby integrated in the first wall device, which in particular has a meandering course at its periphery.
  • cooling channels are arranged distributed uniformly in the circumferential direction. As a result, a uniform cooling over the entire surface of the first wall device can be achieved.
  • a thermal barrier device is arranged between the first wall device and the second wall device, in particular if the second wall device would be in direct thermal contact without a thermal barrier device.
  • the thermal barrier device is made of a material with low thermal conductivity. It can thereby be prevented that a heat conduction path leads from the first wall device directly into the second wall device.
  • the thermal barrier device itself may, for example, be porous, in order, for example, to achieve a transpiration cooling via cooling fluid there.
  • the thermal barrier device is formed for example by a (surface) coating or a tubular element.
  • the thermal barrier device is formed by at least one tubular element. This tubular element can be arranged over the first wall device so as to obtain an effective thermal decoupling from the second wall device.
  • the fibers of high thermal conductivity are C-fibers. These fibers are obtained in the first wall device, that is, it is C paths in the ceramic material from the inside to the outside, which are continuous and uninterrupted.
  • the first wall device comprises a plurality of axially successively arranged segments.
  • a rotationally symmetrical combustion chamber can be produced in a simple manner. It is in this context on the EP 1 748 253 A2 referenced, to which reference is expressly made.
  • adjacent segments have different fiber orientations in a fiber reinforcement matrix.
  • a first wall device which has a high thermal resistance with low thermal expansion.
  • segments or segment groups are axially braced in the second wall device positioned.
  • a corresponding combustion chamber device can be produced in a simple manner.
  • the first wall device is at least partially fluid-impermeable. As a result, a regenerative cooling can be effectively achieved.
  • the cooling fluid absorbs heat and dissipates it. With a partial fluid permeability by providing corresponding channels or pores, a transpiration cooling effect can be achieved at certain points.
  • a fluid impermeability can be achieved, for example, by virtue of the fact that the first wall device has a fluid-impermeable coating on the outside. For example, a copper coating is provided.
  • the material of the first wall device has closed pores or is free of pores. During the production of the first wall device, care is taken to ensure that it is free from pores or that the resulting pores are closed by appropriate impregnation.
  • a volume fraction of high thermal conductivity fibers of the first wall device reaches at least 30%, in particular at least 40%, in particular at least 50%, preferably at least 60% and preferably at least 65% or at least 70%.
  • a high integral thermal conductivity of, for example, more than 300 W / mK can be achieved by the first wall device.
  • combustion chamber or pusher chamber is rotationally symmetrical to an axial axis. This results in effective flow conditions.
  • the first wall device is produced in particular from a carbide-ceramic or oxide-ceramic material or highly heat-conductive carbon material (such as C / C).
  • the carbide-ceramic material may be, for example, a C-XC or C / C-XC carbide material where X is a carbide former such as silicon.
  • the second wall device is made of a fiber composite material.
  • the combustion chamber device can thereby be produced with a low weight.
  • the coating material used is a material with high temperature resistance and the highest possible thermal conductivity. This avoids "hot spots" with the corresponding material problems.
  • a ceramic material is used. As a result, a higher temperature gradient can be built up via the first wall device in order to ensure effective heat transport.
  • the first wall device is coated on the outside.
  • a fluid impermeability of the first wall device can be achieved. It is thereby also possible, when a material of high thermal conductivity, such as a metallic material such as copper, is used as the coating material to ensure uniform heat distribution on the outside of the first wall device.
  • cooling fluid for example, hydrogen or methane is used.
  • the correspondingly preheated cooling fluid can then be used as fuel.
  • a first embodiment of a combustion chamber device which in a sectional view schematically in FIG. 1 and designated therein by 10, comprises a combustion chamber designated as a whole by 12.
  • the combustion chamber has a combustion chamber 14.
  • This combustion chamber 14 is in particular rotationally symmetrical to an axial axis 16 is formed.
  • the combustion chamber 12 is assigned a suitable injector device 46, through which fuel and oxidizer are blown into the combustion chamber 14.
  • In the combustion chamber 14 is a combustion for the corresponding thrust generation.
  • the combustion chamber device 10 has a nozzle device 18, which in a main flow direction 20 (see FIG FIG. 4 ) connects to the combustion chamber.
  • the nozzle device 18 has a nozzle chamber 22, which is rotationally symmetrical with an axis which is coaxial with the axial axis 16.
  • the nozzle device 18 has a cross-sectional constriction 24 in comparison to the cross section of the combustion chamber 14, to which an extension 26 connects. Via the nozzle device 18, a corresponding thrust is generated by means of combustion gases produced during combustion.
  • a combustion chamber device is a special case of a thrust chamber device.
  • a thrust chamber device can produce a thrust, whereby combustion does not necessarily have to take place for thrust generation.
  • gases in a push chamber of a push chamber device may be heated via nuclear decomposition processes.
  • combustion chamber and thrust chamber are basically the same.
  • the combustion chamber 12 comprises a first wall device 28.
  • the first wall device is made of a ceramic composite material (CMC material; Ceramic Matrix composite material).
  • the first wall device 28 has an inner side 30, which limits the combustion chamber 14. It also has an inner side opposite outer side 32.
  • the first wall device 28 extends along the axial axis 16. It is formed along this axial axis 16 closed. In FIG. 1 For purposes of illustration, three segment groups 34a, 34b, 34c are shown as not connected. In fact, the individual segment groups are connected to each other, so that the first wall device 28 forms an inner liner (inner shell) for the combustion chamber 14.
  • the segment groups can be permanently connected to one another, for example by adhesive bonding or ceramic joining, or they can be detachably connected to one another; For example, they can be clamped by an axial clamping pressure.
  • the combustion chamber device 10 comprises a second wall device 36, which is closed and surrounds the first wall device 28.
  • the second wall device 36 has an inner side 38, which faces the outer side 32 of the first wall device 28.
  • the second wall means 36 is an outer liner (outer shell) of the combustion chamber device 10.
  • the combustion chamber 12 with the first wall means 28 is arranged in the second wall means 36, which is formed closed.
  • the first wall device 28 is seated in an embodiment between an end face 42 of the nozzle device 18 and an end face 44 of an injector 46.
  • the injector 46 is in turn held by a flange 48 which is fixed via connecting elements 50 such as bolts or the like to the second wall means 36.
  • the end faces 42 and 44 are in particular formed as annular surfaces. Between these sits the first wall means 28 axially clamped.
  • the material of the first wall device 28 has a smaller (in particular substantially lower) modulus of elasticity in the axial direction compared to a radial direction 52 perpendicular thereto.
  • a type of axial "spring action" can be achieved and the first wall device 28 can be axially biased between the end faces 42 and 44.
  • the first wall device 28 can thereby be inserted loosely and a mechanical decoupling from the second wall device can also be achieved.
  • a cooling channel device designated as a whole by 54 which comprises one or more cooling channels 56, through which a cooling channel fluid can be flown past the outside 32 of the first wall device 28 in order to achieve regenerative cooling of the first wall device 28.
  • the cooling channel 56 or the cooling channels 56 are formed as recesses on the second wall means 36 on the inside 38 or formed between the first wall means 28 and the second wall means 36 and run along the outside 32 along the first wall means 28.
  • a corresponding cooling channel 56 is oriented at least approximately parallel to the axial axis 16.
  • a plurality of spaced-apart cooling channels 56 can be provided which are arranged distributed circumferentially around the first wall device 28 and in particular are distributed uniformly. It is also possible that a cooling channel 56 is provided, which surrounds the first wall device 28 in an annular manner.
  • the first wall device 28 comprises a plurality of segments 58 which are arranged one after the other in the axial direction 16 and which are, in particular, ring segments. Adjacent segments 58 are connected to each other and in particular integrally connected to each other. In this case, a plurality of segments 58 can be connected to segment groups 34a, 34b, 34c, whereby adjacent segment groups 34a, 34b or 34b, 34c are in turn connected to each other and in particular are integrally connected to each other.
  • segments 58 and then a segment group 34a, etc. made of ceramic composite material by first layers 60 of a precursor material are made.
  • the layers 60 comprise fiber webs (or fiber webs or fiber webs 62) with, for example, fibers oriented perpendicular to one another.
  • FIG. 2 (b) are 0 ° / 90 ° fiber web 62 indicated.
  • Adjacent layers 60 have a different fiber orientation. For example, the fiber orientation with respect to adjacent layers is ⁇ 45 °. This is in FIG. 2 (b) indicated.
  • a scrim 64 adjacent the scrim is also a 0 ° / 90 ° fiber scrim with a ⁇ 45 ° orientation.
  • the layers 60 can be oriented at arbitrary angles to one another.
  • the individual fibers within a layer 60 may be oriented at arbitrary angles to one another.
  • Such a stack 66 ( FIG. 2 (a) ) is infiltrated with a carbon precursor material and in particular a resin material or the fiber webs 62 are already provided with such a carbon precursor material (prepreg scrim).
  • a precursor segment group 68 is then cut out after curing of the carbon precursor material.
  • the cutting can be done before pyrolysis of the stack 66 or after pyrolysis.
  • the precursor segment group 68 is a resin fiber fabric body (resin fiber fabric body, resin fiber knit fabric, etc.). If cleavage occurs after pyrolysis, then the precursor segment group body is a carbon body.
  • the corresponding carbon body after pyrolysis is then ceramified.
  • a ceramization by means of the LSI process liquid silicon infiltration
  • This liquid silicon reacts with carbon to form silicon carbide.
  • a carbide-ceramic C / C-SiC body is then formed when the fibers of the fiber scrims 62, 64 were carbon fibers and a precursor polymer plastic matrix was converted to carbon.
  • a C-SiC material is usually produced. In such ceramization processes, the carbon fibers react only marginally with the silicon.
  • first wall device 38 in one piece or to produce a plurality of segment groups 34a, 34b, 34c. It is also possible to prepare various precursor segment-group bodies, which are then joined to one another, for example during ceramization, or glued for example.
  • the segment groups 34a, 34b, 34c and precursor segment group body 68 can be clamped axially against each other with guaranteed centering only by external tension.
  • FIG. 3 (a) a section of the combustion chamber 12 is shown.
  • FIG. 3 (b) a section of the first wall means is shown schematically. Different segments 58 have different fiber orientations (cf. FIG. 2 (b) ).
  • fibers 70 of high thermal conductivity are arranged in the first wall device 28.
  • the Thermal conductivity (integral) is at least 100 W / mK and preferably at least 300 W / mK. For example, it can reach 1000 W / mK or more.
  • the fibers 70 of high thermal conductivity are aligned in a heat transport direction 72 of the combustion chamber 14 (or pusher chamber) away.
  • the fibers 70 of high thermal conductivity are, for example, C-fibers. They are obtained as fibers in the first wall device 28. The C fibers are retained during pyrolysis. An oxidation protection for the operational use can be achieved if required by ceramization with Carbidsentner, or by introducing additional oxidic fiber components or matrix components.
  • the high thermal conductivity fibers 70 extend from the inner side 30 to the outer side 32 into a cooling channel 56.
  • a corresponding fiber 70 terminates with a corresponding fiber end on the inner side 30 and with the opposite fiber end in a flow space 74 of the corresponding channel 56.
  • the respective fiber ends can In this case, ends directly on the inside 30 or outside 32 or there may still be a corresponding coating there, as will be explained in more detail below.
  • High thermal conductivity fibers 70 are oriented transversely, and more preferably perpendicularly, to the axial axis 16. Fibers 70 of high thermal conductivity are in particular radially (ie parallel to the radial direction 52) oriented. In particular, most of the high thermal conductivity fibers 70 are oriented in at least approximately the radial direction.
  • the radial direction 52 is a direction in which the distance between the inside 30 and the outside 32 is the smallest.
  • fibers 70 of high thermal conductivity which are not oriented in the radial direction.
  • fibers 70 of high thermal conductivity in the first wall device 28 is at least 30%, preferably at least 40% and in particular preferably at least 50% and preferably at least 55%, or at least 60%, or at least 65%. In one embodiment, the volume fraction is about 70%.
  • the combustion chamber 12 or thrust chamber can be regeneratively cooled in an effective manner.
  • the corresponding wall material in order to prevent overheating of the first wall device 28, the corresponding wall material must have a high temperature resistance and must have a high thermal conductivity.
  • a high local temperature gradient generally means that high thermal stresses are present, which in turn leads to material problems (in particular Material fatigue) can lead.
  • a ceramic composite has high temperature resistance and low thermal expansion. The combination of high temperature resistance, high thermal conductivity and low thermal brittleness allows high temperature gradients across the wall profile from the hot gas side to the cooling channel 56. High temperature gradients also allow for a certain and necessary heat dissipation into the first wall means 28 at already lower heat conductivities and wall thicknesses for example, in metallic wall structures.
  • fibers 70 of high thermal conductivity to provide defined heat transport paths and thus increase the integral thermal conductivity, a high cooling efficiency is obtained with high structural integrity.
  • the first wall device 28 is formed fluid-tight. This can be achieved in different ways.
  • the first wall means 28 has a fluid impermeable coating on the outside 82.
  • the material of the first wall device 28 it is possible for the material of the first wall device 28 to have closed pores, or to be free of pores. If there are pores, they can be closed by a suitable impregnation. It can be ensured, for example, during the ceramization that the ceramic material is pore-free or has closed pores.
  • the first wall device 28 is partially permeable between the combustion chamber 14 (or thrust chamber) and the cooling channel device 54.
  • cooling fluid which is in particular fuel such as hydrogen
  • a certain proportion of perspiration can take place through the first wall device 28 in certain areas.
  • a transpiration cooling can take place at these specific areas and, for example, a film of cooling fluid can form on the inside 30 of the first wall device 28 in certain areas.
  • a film of cooling fluid can form on the inside 30 of the first wall device 28 in certain areas.
  • Such a film reduces, for example, the wall friction and thereby reduces throttle losses. It can, as explained, also take place an additional cooling effect via transpiration cooling.
  • the inside 30 and the outside 32 can be easily sanded and coated, since fiber ends on the inside 30 and the outside 32 end. This can not lead to the splicing of fibers.
  • An abrasive surface then has a homogeneous roughness.
  • coatings can be applied with good adhesion. For example, sputtered layers, plasma coatings, electroplated coatings, etc. can then be produced.
  • the outside 32 is provided with a coating 76, as in FIG. 3 (c) indicated, provided.
  • the coating 76 is in particular made of a metallic material and extends over the entire outer side 32.
  • the coating 76 of a metallic material of high thermal conductivity such as copper, it is achieved that a homogeneous temperature distribution is formed on the outer side 32 of the first wall device 28. In turn, local peak loads on the material of the first wall device 28 are prevented.
  • the inner side 30 may be provided with a coating 78 (cf. FIG. 3 (c) ) be provided.
  • This coating is preferably made of a material with high heat transfer to the first wall device 28.
  • it is made of a ceramic material (carbide-ceramic or oxide-ceramic).
  • a ceramic material is silicon carbide, for example.
  • the fibers 70 in the first wall means 28 are effectively protected in a matrix, the ceramic composite, protected.
  • the first wall means 28 may be made of, for example, a carbide-ceramic material. It can also be made, for example, from an oxide ceramic material.
  • Cooling fluid in particular hydrogen
  • the cooling fluid absorbs heat provided via the first wall device 28 and is preheated.
  • the preheated cooling fluid is then injected via the injector device 46 into the combustion chamber 14 when it is fuel.
  • the cooling fluid is, for example, hydrogen and in particular liquid hydrogen. Heat is effectively dissipated from the inner side 30 to the outer side 32 of the first wall device 28 via the high thermal conductivity fibers 70.
  • the flow direction 84 can also be executed in the reverse direction.
  • turbopumps that is fuel, which in the corresponding (regenerative) cooling channel device, which associated with a combustion chamber or thrust chamber is heated, gives the absorbed enthalpy while flowing through a turbine to this before the Fuel in an injection head is injected into the combustion chamber.
  • a turbo pump is then operated during the expander cycle.
  • a flow direction of the cooling fluid may be parallel to the main flow direction of a hot gas flow in the combustion chamber (co-flow) or opposite (counter-flow).
  • a first wall means 88 which defines a rotationally symmetrical about the axial axis 16 (for the same elements as in the combustion chamber 12 are used reference numerals) the combustion chamber 90.
  • the first wall device is made of a ceramic composite material. It has an inner side 92, which delimits the combustion chamber, and an outer side 94. In the region of the outer side 94, cooling channels 96 of the cooling channel device 54 are formed in the first wall device 88.
  • the cooling channels 96 are arranged circumferentially on the outer side 94. Adjacent cooling channels 96a, 96b are circumferentially spaced from one another with an intermediate web 98. In particular, the cooling channels 96 are arranged evenly distributed around the circumference of the first wall device 88 on the outer side 94.
  • the cooling channels 96 are integrated into the first wall device 88.
  • the first wall device 88 is correspondingly meander-shaped on the outer side 94.
  • a coating On the inside 92 and / or the outside 94 can be provided as described above, a coating.
  • the cooling channels 96 are oriented parallel to the axial axis 16.
  • a thermal barrier device 100 may be provided. This is arranged around the outside 94 of the first wall device 88.
  • the thermal barrier device can be a high heat input in a second wall means surrounding the first wall means 88 prevent. In principle, such high heat input can take place via the webs 98.
  • the thermal barrier device 100 lies between an outer side of the webs 98 and the second wall device as an outer liner.
  • the thermal barrier device 100 is formed, for example, by a tubular element 102, which is pushed over the first wall device 84.
  • the thermal barrier device 100 provides a thermal insulation layer. It is made for example of a poor heat conductive fiber ceramic material, for example, based on alumina.
  • this thermal barrier device has a certain open porosity. Then this thermal barrier device 100 can be saturated by "cold” cooling fluid and additionally cooled.
  • the combustor 86 functions as described above.
  • the combustion chamber device according to the invention is for example part of a drive device of a missile and in particular a rocket.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
EP12179345.9A 2011-08-04 2012-08-06 Dispositif de chambre de combustion ou dispositif de chambre de poussée Active EP2554904B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011052413A DE102011052413A1 (de) 2011-08-04 2011-08-04 Brennkammervorrichtung oder Schubkammervorrichtung

Publications (3)

Publication Number Publication Date
EP2554904A2 true EP2554904A2 (fr) 2013-02-06
EP2554904A3 EP2554904A3 (fr) 2017-12-20
EP2554904B1 EP2554904B1 (fr) 2020-09-23

Family

ID=47002558

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12179345.9A Active EP2554904B1 (fr) 2011-08-04 2012-08-06 Dispositif de chambre de combustion ou dispositif de chambre de poussée

Country Status (2)

Country Link
EP (1) EP2554904B1 (fr)
DE (1) DE102011052413A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114459057B (zh) * 2022-01-18 2023-03-24 中国航发四川燃气涡轮研究院 陶瓷基火焰筒连接结构及燃气涡轮发动机燃烧室

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1748253A2 (fr) 2005-07-26 2007-01-31 Deutsches Zentrum für Luft- und Raumfahrt e.V. Chambre de combustion et procédé de fabrication d'une chambre de combustion

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5780157A (en) * 1994-06-06 1998-07-14 Ultramet Composite structure
DE19730674A1 (de) * 1997-07-17 1999-01-21 Deutsch Zentr Luft & Raumfahrt Brennkammer und Verfahren zur Herstellung einer Brennkammer
US6783824B2 (en) * 2001-01-25 2004-08-31 Hyper-Therm High-Temperature Composites, Inc. Actively-cooled fiber-reinforced ceramic matrix composite rocket propulsion thrust chamber and method of producing the same
DE102005059502A1 (de) * 2005-12-06 2007-06-14 Deutsches Zentrum für Luft- und Raumfahrt e.V. Heißkammer
DE102008020198B8 (de) * 2008-04-15 2015-05-13 Astrium Gmbh Düsenerweiterung für ein Triebwerk und Verfahren zur Herstellung und Kühlung einer Düsenerweiterung
DE102009028470B4 (de) * 2009-08-12 2011-07-28 Deutsches Zentrum für Luft- und Raumfahrt e.V., 51147 Absorbervorrichtung

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1748253A2 (fr) 2005-07-26 2007-01-31 Deutsches Zentrum für Luft- und Raumfahrt e.V. Chambre de combustion et procédé de fabrication d'une chambre de combustion

Also Published As

Publication number Publication date
EP2554904B1 (fr) 2020-09-23
DE102011052413A1 (de) 2013-02-07
EP2554904A3 (fr) 2017-12-20

Similar Documents

Publication Publication Date Title
EP0927299B1 (fr) Chambre de combustion et procede permettant de realiser une chambre de combustion
DE60224412T2 (de) Keramikmatrix-verbundstruktur mit integriertem kühlkanal und herstellungsverfahren
DE69916240T2 (de) Wärmetauscher aus verbundwerkstoff und dessen herstellungsverfahren
DE60224691T2 (de) Keramisches hybridmaterial aus keramischen isolier- und konstruktionsschichten
DE102011050757B4 (de) Brennkammerflammrohrkühlsystem
EP0913373B1 (fr) Matériau composite céramique renforcé par des fibres de carbone
WO1999027304A1 (fr) Chambre de combustion et procede de refroidissement par vapeur d'une chambre de combustion
DE69622226T2 (de) Hybride Verbundwerkstücke und Geschossbauteile und ihre Herstellung
DE10126926B4 (de) Brennkammer mit Innenmantel aus einem keramischen Komposit-Material und Verfahren zur Herstellung
EP1748253B1 (fr) Chambre de combustion et procédé de fabrication d'une chambre de combustion
US11845699B2 (en) Methods for manufacturing coated composite materials
DE102010043336B4 (de) Brennkammervorrichtung
EP2554904B1 (fr) Dispositif de chambre de combustion ou dispositif de chambre de poussée
DE102004029029B4 (de) Einspritzkopf
EP1939529A1 (fr) Revêtement de chambre de combustion CMC à structure à double couche
EP2227629B1 (fr) Dispositif de chambre de combustion
DE69002215T2 (de) Raketenbrennkammer.
Cavalier et al. Composites in aerospace industry
DE19937812A1 (de) Bauelement mit einem bei erhöhter Temperatur belastbaren Teil aus Verbundwerkstoff mit Fluidumwälzkühlung
DE102008020198B4 (de) Düsenerweiterung für ein Triebwerk und Verfahren zur Herstellung und Kühlung einer Düsenerweiterung
DE10230231B4 (de) Mehrschichtiger Verbundwerkstoff
DE102014100345B4 (de) Verfahren zur Herstellung einer Schubkammervorrichtung, Schubkammervorrichtung und Raketentriebwerk
DE102023002467A1 (de) Abgaskrümmer, Zylinderkopf und Verfahren zur Auslegung von Abgaskrümmern
DE102017129321A1 (de) Brennkammervorrichtung, Fahrzeug
Kitamura et al. Fabrication of carbon-carbon composite ion thruster grids-improvement of structural strength

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F23M 5/08 20060101ALI20171115BHEP

Ipc: F23R 3/00 20060101AFI20171115BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180618

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20191008

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20200420

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502012016364

Country of ref document: DE

Ref country code: AT

Ref legal event code: REF

Ref document number: 1316764

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201015

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201224

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201223

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201223

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200923

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210125

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210123

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502012016364

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

26N No opposition filed

Effective date: 20210624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210831

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20210806

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210806

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210806

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210806

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1316764

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210806

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210806

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20120806

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20250709

Year of fee payment: 14

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923