Combustion chamber device, vehicle and method for operating a combustion chamber device

Abstract

Combustion chamber device, comprising a combustion chamber (12) which is delimited by an inner shell (14; 14'), wherein the inner shell (14; 14') has a fluid-permeable structural material (32) and a fluid-impermeable inner shell layer (62), and wherein the inner shell (14; 14') comprises at least one flow channel (42) with a flow region (54) for fluid, characterized in that the fluid-impermeable inner shell layer (62) is arranged on one side (58) of the structural material (32) of the inner shell (14;14') and is integrally connected to the structural material (32), wherein the side (58) delimits the flow region (54) of the at least one flow channel (42) at least in some regions, that the fluid-impermeable inner casing layer (62) has at least one opening (64) by means of which a fluid-effective connection can be established between the flow region (54) of the at least one flow channel (42) and the fluid-permeable structural material (32) of the inner casing (14; 14'), that a diaphragm device (68; 68') with at least one diaphragm element (70) which is assigned to the at least one opening (64) is provided, by means of which the fluid effectiveness of the connection between the at least one flow channel (42) and the structural material (32) of the inner casing (14;14') is controllable and / or regulatable, and that the at least one diaphragm element (70) is arranged between the at least one opening (64) of the fluid-impermeable inner jacket layer (62) and the flow region (54) of the at least one flow channel (42), wherein the at least one diaphragm element (70) has a fluid-impermeable region (72) and at least one inflow channel (74) for fluid, which runs through the fluid-impermeable region (72);

Description

[0001] The invention relates to a combustion chamber device comprising a combustion chamber which is delimited by an inner shell, wherein the inner shell has a fluid-permeable structural material and a fluid-impermeable inner shell layer, and wherein the inner shell comprises at least one flow channel with a flow region for fluid.

[0002] The invention further relates to a vehicle, in particular a missile.

[0003] The invention further relates to a method for operating a combustion chamber device.

[0004] WO 99 / 04156 A1 discloses a combustion chamber comprising a combustion chamber, an inner shell surrounding the combustion chamber, an outer shell surrounding the inner shell, and coolant channels formed between the outer shell and the inner shell. A region of the inner shell may have a coating of a TBC material on its inner side.

[0005] DE 199 01 424 A1 discloses a hot gas chamber with an inner wall permeable to coolant for the purpose of transpiration cooling and a coolant supply device associated therewith.

[0006] DE 10 2005 059 502 A1 discloses a hot chamber comprising at least one hot space, at least one hot chamber wall defining the hot space, and at least one shell structure surrounding the hot chamber wall and / or being surrounded by the hot chamber wall. A shell is arranged between the hot chamber wall and the shell structure, which at least partially abuts the hot chamber wall and the shell structure. The shell is designed to be expandable in a spacing direction between the hot chamber wall and the shell structure and in a direction transverse to this spacing direction.

[0007] DE 10 2005 036 137 A1 discloses a combustion chamber comprising an outer shell and an inner shell defining a combustion chamber and fluid-permeable for effusion cooling or transpiration cooling. The inner shell comprises a plurality of disk elements arranged successively along an axial axis.

[0008] DE 10 2010 043 336 A1 discloses a combustion chamber device comprising a combustion chamber, an injection head for supplying at least one fluid to the combustion chamber device, and a nozzle extension adjoining the combustion chamber. The combustion chamber device comprises a casing, which at least partially forms a wall of the combustion chamber and a wall of the nozzle extension and, in the assembled state of the combustion chamber device, extends substantially from the injection head to an end of the nozzle extension facing away from the injection head.

[0009] DE 693 02 042 T2 discloses a container containing hot gases and cooled by transpiration, comprising a porous wall forming the inner part of the container, and means for applying a cooling fluid to the outer surface of the porous wall, thereby creating a transpiration cooling fluid flow through the porous wall.

[0010] The invention is based on the object of providing a combustion chamber device of the type mentioned above which has high performance and high reliability while being easy to manufacture.

[0011] This object is achieved according to the invention in the combustion chamber device mentioned at the outset in that the fluid-impermeable inner shell layer is arranged on one side of the structural material of the inner shell and is integrally connected to the structural material, wherein the side delimits the flow area of ​​the at least one flow channel at least in some areas, that the fluid-impermeable inner shell layer has at least one opening by means of which a fluid-effective connection can be established between the flow area of ​​the at least one flow channel and the fluid-permeable structural material of the inner shell, that a baffle device with at least one baffle element, which is assigned to the at least one opening, is provided by means of which the fluid effectiveness of the connection between the at least one flow channel and the structural material of the inner shell can be controlled and / or regulated,and that the at least one diaphragm element is arranged between the at least one opening of the fluid-impermeable inner jacket layer and the flow region of the at least one flow channel, wherein the at least one diaphragm element has a fluid-impermeable region and at least one inflow channel for fluid which runs through the fluid-impermeable region.

[0012] The combustion chamber device includes, for example, an injection device for supplying fluids to the combustion chamber. This injection device can be used to supply, for example, fuel and oxidizer for combustion.

[0013] During operation of the combustion chamber, high pressures and temperatures arise due to the chemical reaction of the fluids within the combustion chamber. This places particularly high thermal stress on the inner shell of the combustion chamber. For this reason, effective and efficient cooling processes are necessary to cool the combustion chamber.

[0014] In the combustion chamber device according to the invention, it is provided that the cooling of the inner shell takes place in particular by means of effusion cooling or transpiration cooling.

[0015] For this purpose, a cooling medium is supplied to the fluid-permeable structural material of the inner shell via the at least one flow channel. The cooling medium flows (at least partially) from the at least one flow channel into the fluid-permeable structural material of the inner shell. Due to the fluid permeability of the structural material of the inner shell, the cooling medium reaches, for example, an inner side of the inner shell facing the combustion chamber, where it forms an at least approximately homogeneous cooling film (effusion cooling).

[0016] In transpiration cooling, the cooling medium also undergoes a phase change. This can be achieved, in particular, by selecting the appropriate cooling medium.

[0017] Using the cooling methods mentioned, the combustion chamber device can be cooled effectively and efficiently.

[0018] The inner shell and / or the structural material of the inner shell is made, for example, of a ceramic fiber composite material.

[0019] The inner shell defines the combustion chamber. "Defining" in this context means that the inner shell surrounds and / or encloses the combustion chamber, and in particular, completely surrounds and / or encloses it. The inner shell is, for example, shaped like a hollow cylinder.

[0020] A fluid-impermeable inner shell layer is arranged on one side of the inner shell. This side (and the inner shell layer arranged on the side) surround and / or delimit the flow area of ​​the at least one flow channel. The fluid-impermeable inner shell layer fundamentally prevents fluid from the flow area of ​​the at least one flow channel from penetrating the structural material of the inner shell.

[0021] The fluid-impermeable inner shell layer has at least one opening through which a fluid-effective connection can be established between the flow region of the at least one flow channel and the fluid-permeable structural material of the inner shell. For example, cooling medium can flow from the flow region into the structural material of the inner shell through the at least one opening.

[0022] By means of the fluid-impermeable inner shell layer, for example, a fluid flow from the flow area of ​​the at least one flow channel into the structural material of the inner shell can be controlled. The strength of the fluid flow can thus be controlled and / or regulated, for example, in conjunction with an orifice device.

[0023] Openings within the fluid-impermeable inner shell layer can be positioned in different areas of the combustion chamber device. This allows the cooling of the inner shell of the combustion chamber device to be restricted, for example, to specific spatial areas that are subject to particularly high thermal stress. The cooling mechanisms described above can therefore be used particularly flexibly.

[0024] The fluid-impermeable inner jacket layer is, in particular, bonded to the structural material of the inner jacket. For example, it is bonded to the structural material of the inner jacket. The fluid-impermeable inner jacket layer is, for example, electroplated to the structural material of the inner jacket.

[0025] It is advantageous if an outer shell surrounds the outer side of the inner shell facing away from the combustion chamber. This provides thermal and spatial insulation between the inner shell and the combustion chamber. This also increases the stability of the combustion chamber device.

[0026] For example, the outer shell comprises a fiber-reinforced plastic, particularly a carbon-fiber-reinforced plastic. This allows for effective thermal shielding of the internal components of the combustion chamber device while maintaining high stability.

[0027] It is advantageous if the flow area of ​​the at least one flow channel is at least partially delimited by an inner side of the outer casing facing the inner casing. The at least one flow channel can thus be implemented on the combustion chamber device or on the inner casing in a technically simple manner.

[0028] For the same reason, it is advantageous if the at least one flow channel is positioned between an outer side of the inner shell facing the outer shell and an inner side of the outer shell facing the inner shell.

[0029] It is advantageous if the fluid-impermeable inner shell layer has a plurality of openings spaced parallel to a longitudinal direction of the at least one flow channel. This allows fluid from the flow region of the at least one flow channel to be uniformly supplied to the structural material of the inner shell.

[0030] The longitudinal extension direction of the at least one flow channel is in particular parallel to a longitudinal extension axis of the inner shell.

[0031] The combustion chamber device comprises an orifice device by means of which the fluid effectiveness of the connection between the at least one flow channel and the structural material of the inner shell can be controlled and / or regulated. This allows, for example, the strength of a fluid inflow from the flow region of the at least one flow channel into the structural material of the inner shell to be controlled and / or regulated. This allows, for example, a cooling capacity to be adjusted depending on a temperature and / or power state of the combustion chamber device. In this way, the efficiency of the combustion chamber device is increased.

[0032] In particular, the fluid effectiveness of the connection between the at least one flow channel and the structural material of the inner shell can be continuously controlled and / or regulated by means of the aperture device.

[0033] The diaphragm device comprises at least one diaphragm element arranged between the at least one opening of the fluid-impermeable inner shell layer and the flow region of the at least one flow channel, wherein the at least one diaphragm element has a fluid-impermeable region and at least one inflow channel for fluid, which runs through the fluid-impermeable region. As a result, for example, the fluid effectiveness of the connection between the at least one flow channel and the structural material of the inner shell can be easily controlled and / or regulated. The fluid effectiveness of the connection is then dependent, for example, on a position of the at least one diaphragm element relative to the at least one opening of the fluid-impermeable inner shell layer.

[0034] The aperture device and / or the at least one aperture element of the aperture device is made, for example, of a metallic material or comprises a metallic material. The aperture device and / or the at least one aperture element is made, for example, of a copper material or comprises a copper material.

[0035] In particular, the at least one inflow channel of the at least one diaphragm element is arranged displaceably relative to the at least one opening of the fluid-impermeable inner shell layer. The control and / or regulation of the fluid effectiveness of the connection between the at least one flow channel and the structural material of the inner shell can thus be implemented in a technically simple manner using the at least one diaphragm element.

[0036] The at least one aperture element is arranged, for example, to be displaceable parallel to a longitudinal direction of the at least one flow channel.

[0037] In one embodiment, the diaphragm device has at least one holding element on which one or more diaphragm elements are arranged. In particular, an adjustment element is arranged on the at least one holding element, by means of which the at least one holding element can be displaced with the diaphragm elements. For example, a plurality of diaphragm elements can be arranged on the at least one holding element. By means of the adjustment element, for example, all diaphragm elements of the diaphragm device can be displaced simultaneously. This enables uniform control and / or regulation of the fluid effectiveness of the connection between the at least one flow channel and the structural material of the inner casing.

[0038] The adjustment element is in particular arranged at one end of the at least one holding element and / or integrally connected to the at least one holding element.

[0039] The adjusting element comprises, for example, an adjusting ring on which one or more holding elements are arranged.

[0040] It is advantageous if each inflow channel of the at least one diaphragm element is assigned to an opening in the fluid-impermeable inner shell layer. A possible fluid flow from the flow region of the at least one flow channel through the at least one opening into the structural material of the inner shell can thus be particularly easily controlled and / or regulated using the at least one diaphragm element.

[0041] In particular, the distance between adjacent openings in the fluid-impermeable inner shell layer corresponds to the distance between adjacent inflow channels of the aperture device. This allows the aperture device to be implemented in a particularly simple technical manner.

[0042] It is advantageous if the at least one flow channel has at least one guide element, the at least one diaphragm element has a counter-element corresponding to the at least one guide element, and if the counter-element can be arranged, in particular displaceably, on the at least one guide element. This allows one or more diaphragm elements to be arranged within the at least one flow channel in a particularly simple manner, and in particular, displaceably.

[0043] The at least one guide element comprises, for example, an indentation, and the at least one counter element comprises, for example, a protrusion corresponding to the indentation. The counter element is held displaceably within the guide element, for example, by a one-sided positive fit.

[0044] In one embodiment, the diaphragm device comprises a first group of diaphragm elements arranged in a region of a first end of the at least one flow channel, and the diaphragm device comprises a second group of diaphragm elements arranged in a region of a second end of the at least one flow channel opposite the first end. Fluid inflow from the flow region of the at least one flow channel into the structural material of the inner casing can thereby be restricted to the region of the first end of the at least one flow channel and to the region of the second end of the at least one flow channel. This allows, for example, effusion or transpiration cooling of the inner casing to be limited to the aforementioned regions of the inner casing.

[0045] The first end of the at least one flow channel is arranged, for example, in a region of a first end of the combustion chamber. The second end of the at least one flow channel is arranged, in particular, in a region of a second end of the combustion chamber, which is opposite the first end of the combustion chamber.

[0046] In particular, the at least one flow channel is circumferentially closed. This allows fluid to be guided through the at least one flow channel in a technically simple manner.

[0047] It is advantageous if a longitudinal extension direction of the at least one flow channel is oriented parallel to a longitudinal extension axis of the inner shell. The at least one flow channel can thus be formed on the inner shell in a technically simple manner. The inner shell can thus be designed, for example, with a plurality of flow channels, to be at least approximately rotationally symmetrical. The longitudinal extension axis is, for example, an axis of symmetry of the inner shell. The inner shell is, for example, axially symmetrical and / or rotationally symmetrical to the longitudinal extension axis.

[0048] In an advantageous embodiment of the invention, a plurality of flow channels are provided, which are spaced apart from one another in a circumferential direction of the inner shell, which is transverse and in particular perpendicular to a longitudinal axis of the inner shell. This allows, for example, a uniform fluid flow from the flow channels into the structural material of the inner shell over its entire circumference or part of its circumference. This allows for uniform cooling of the combustion chamber around the circumference.

[0049] The structural material of the inner shell is or comprises in particular a porous material which preferably has a high fluid permeability.

[0050] For example, the fluid-permeable structural material of the inner shell comprises a fiber composite material, and in particular a ceramic fiber composite material. These materials are particularly porous and exhibit good fluid permeability. This allows, for example, effusion or transpiration cooling of the inner shell to be carried out simply and efficiently.

[0051] In one embodiment, the inner shell has a plurality of inner shell elements and / or the inner shell is constructed from a plurality of inner shell elements, wherein the inner shell elements are arranged consecutively parallel to a longitudinal axis of the inner shell. The inner shell can thus be designed as a hybrid. This allows, for example, a combination of regenerative and transpiration cooling to be achieved.

[0052] The inner shell elements are in particular each ring-shaped and / or circular.

[0053] In particular, it can be provided that the inner shell elements surround and / or enclose the combustion chamber and / or the longitudinal axis of the inner shell.

[0054] The inner shell elements are arranged and / or configured, for example, rotationally symmetrical to the longitudinal axis of the inner shell. For example, the respective centers of annular and / or circular inner shell elements lie on the longitudinal axis of the inner shell.

[0055] In particular, it can be provided that the inner shell comprises inner shell elements of different types and / or different kinds. The different inner shell elements have, for example, different physical properties, such as different thermal conductivities and / or different fluid permeabilities.

[0056] It can be advantageous if adjacent inner shell elements are each made of different materials or comprise different materials. The different inner shell elements and / or materials have, for example, different physical properties. The different inner shell elements and / or materials have, for example, different thermal conductivities and / or different fluid permeabilities. This allows several different cooling mechanisms to be implemented on the combustion chamber device.

[0057] In particular, inner shell elements of different types and / or different kinds are arranged alternately and / or alternately parallel to the longitudinal axis.

[0058] For example, inner shell elements of a first type and inner shell elements of a second type are arranged alternately parallel to the longitudinal axis.

[0059] Alternatively or additionally, it is possible for the inner shell to comprise inner shell elements of three or more different types and / or different kinds.

[0060] For example, the inner shell comprises inner shell elements of three different types and / or kinds. The inner shell elements of the first type are made, for example, from a copper material or comprise a copper material. The inner shell elements of the second type are made, for example, from a chromium material or comprise a chromium material. The inner shell elements of the third type are made, for example, from a zirconium material or comprise a zirconium material.

[0061] The respective inner shell elements of different types and / or different kinds are in particular arranged alternately one after the other.

[0062] The inner shell and / or the inner shell elements are manufactured, for example, using a 3D printing process. For example, the respective inner shell elements are manufactured from the copper material and / or chromium material and / or zirconium material using a 3D printing process.

[0063] According to the invention, the vehicle mentioned above comprises a combustion chamber device as described above. The vehicle is, in particular, a missile comprising a combustion chamber device as described above.

[0064] The combustion chamber device is, for example, a component of the missile's engine. The missile can then be propelled by means of the combustion chamber device.

[0065] According to the invention, the combustion chamber device of the method mentioned at the outset comprises a combustion chamber which is delimited by an inner shell, wherein the inner shell has a fluid-permeable structural material and a fluid-impermeable inner shell layer which is integrally connected to the structural material, and wherein the inner shell comprises at least one flow channel with a flow region for fluid, wherein the fluid-impermeable inner shell layer delimits the flow region at least in some regions, and in which a fluid flows through the at least one flow channel, the fluid from the at least one flow channel is at least partially guided through the at least one opening into the structural material of the inner shell, and in which an inflow strength of the fluid from the at least one flow channel into the structural material of the inner shell is determined by an aperture device having at least one aperture element,which is assigned to the at least one opening and is arranged between the at least one opening and the flow area, is controlled and / or regulated.,

[0066] The method according to the invention has the advantages already explained in connection with the combustion chamber device according to the invention.

[0067] Further advantageous embodiments of the method have already been explained in connection with the combustion chamber device according to the invention.

[0068] The following description of preferred embodiments, taken in conjunction with the drawings, serves to further explain the invention. They show: Fig. 1 is a perspective partial sectional view of an embodiment of a combustion chamber device; Fig. 2 a detailed view of section A according to Fig. 1; Fig. 3 is a partial sectional view of the combustion chamber device in a section perpendicular to a longitudinal axis of the combustion chamber device; Fig. 4 a detailed view of an inner shell of the combustion chamber device with a baffle device; Fig. 5 a schematic representation of various settings I to V of an aperture of the aperture device in a plan view of the aperture; Fig. 6 a schematic representation of the aperture settings I to V in a sectional view perpendicular to the aperture; Fig. 7 is a sectional view of another embodiment of a combustion chamber device; Fig. 8 a missile comprising a combustion chamber device; Fig. 9 is a perspective partial sectional view of another embodiment of a combustion chamber device, wherein an inner shell of the combustion chamber device is constructed from a plurality of inner shell elements; and Fig. 10 a detailed view of section A according to Fig. 9.

[0069] An embodiment of a combustion chamber device which is shown in Fig. 1 and designated 10 therein, comprises a combustion chamber 12, which is defined by an inner shell 14. The inner shell 14 is surrounded by an outer shell 16.

[0070] The combustion chamber device 10 serves to combust fluids introduced into the combustion chamber 12. Fluids are introduced into the combustion chamber 12, for example, by means of an injection device 18 (indicated by arrows). For this purpose, the combustion chamber 12 has an inlet opening 22 at a first end 20.

[0071] Combusted fluids, which form a hot exhaust gas, leave the combustion chamber 12 through an outlet opening 24, which is formed at a second end 26 of the combustion chamber 12 opposite the first end 20. This generates thrust, which can be used, for example, to propel a rocket.

[0072] At the second end 26 of the combustion chamber 12, for example, a nozzle and / or a nozzle extension is arranged.

[0073] The combustion chamber device 10 extends along a longitudinal axis 28. The combustion chamber device 10 is in particular designed to be substantially rotationally symmetrical with respect to the longitudinal axis 28.

[0074] The inner shell 14 and / or the outer shell 16 are, for example, hollow-cylindrical in shape.

[0075] The combustion chamber 12 is completely defined by the inner shell 14. The inner shell 14 defines the combustion chamber 12 in a radial direction 30, wherein the radial direction 30 is oriented perpendicular to the longitudinal axis 28.

[0076] The inner shell 14 has a fluid-permeable structural material 32. An inner side 34 of the structural material 32 faces the combustion chamber 12.

[0077] The fluid-permeable structural material 32 of the inner shell 14 is or comprises, for example, a fiber composite material. The structural material 32 comprises, in particular, a ceramic fiber composite material. The structural material 32 has, in particular, a high porosity.

[0078] Furthermore, the structural material 32 of the inner shell 14 has, in particular, a high thermal conductivity.

[0079] The outer shell 16 radially surrounds the inner shell 14. An outer side 36 of the inner shell 14 facing away from the combustion chamber 12 faces an inner side 38 of the outer shell 16.

[0080] The outer casing 16 is made, in particular, of a fluid-impermeable material. It is made, for example, of a fiber-reinforced plastic, and in particular of a carbon-fiber-reinforced plastic.

[0081] In the embodiment shown, the outer shell 16 forms the radially outermost layer of the combustion chamber device 10. An outer side 40 of the outer shell 16 faces away from the inner shell 14 and the combustion chamber 12.

[0082] A plurality of flow channels 42 are formed on the outer side 36 of the inner shell 14. A flow channel 42 runs parallel to a longitudinal direction 44. This longitudinal direction 44 is oriented, in particular, parallel to a longitudinal axis 46 of the inner shell 14. In the illustrated embodiment, the longitudinal axis 46 of the inner shell 14 corresponds to the longitudinal axis 28 of the combustion chamber device 10.

[0083] Adjacent flow channels 42 are spaced apart from one another, for example, on the outer side 40 of the inner shell 14 in a circumferential direction 48 of the inner shell 14. The circumferential direction 48 is perpendicular to the longitudinal axis 46 and perpendicular to the radial direction 30.

[0084] The flow channels 42 have, for example, indentations 50 which are formed on the outer side 36 of the inner casing 14 (cf. Fig. 2 and Fig. 3). These indentations 50 have, for example, a U-shaped cross-section (in a cross-sectional direction perpendicular to the longitudinal axis 28).

[0085] Adjacent flow channels 42a, 42b are separated from one another, for example, on the outer side 40 of the inner shell 14 by intermediate elements 52. An intermediate element 52 is, in particular, integrally connected to the structural material 32 of the inner shell 14. The intermediate element 52 is formed, for example, from the structural material 32 of the inner shell 14.

[0086] A flow channel 42 has a flow region 54 which is formed in an interior space 56 of the flow channel 42.

[0087] The interior space 56 of the flow channel 42 is circumferentially delimited.

[0088] The interior space 56 of the flow channel 42 is bounded by a side 58 of the inner shell 14 facing the structural material 32 of the inner shell 14. The side 58 is, for example, a partial region of the outer side 36 of the inner shell 14.

[0089] On a side facing away from the inner shell 14, the interior space 56 of the flow channel 42 is delimited by the inner side 38 of the outer shell 16.

[0090] In this way, a flow channel 42 is formed between a partial area of ​​the outer side 36 of the inner shell 14 and a partial area of ​​the inner side 38 of the outer shell 16.

[0091] The intermediate elements 52 each have sides 53, which are partial regions of the outer side 36 of the inner shell 14 and which face the inner side 38 of the outer shell 16. The side 53 of an intermediate element 52 bears, in particular, against a partial region of the inner side 38 of the outer shell 16.

[0092] The flow channels 42 serve for cooling during operation of the combustion chamber device 10. In particular, the structural material 32 of the inner shell and the outer shell 16 can be cooled by means of the flow channels 42. For this purpose, a cooling medium, for example, is guided through the flow region 54 of the flow channels 42.

[0093] The flow channels 42 can alternatively or additionally be used to supply a fluid to the injection device 18. For example, fuel or oxidizer can be supplied to the injection device 18 via the flow channels 42. In this case, the fluid is supplied to the injection device 18 in a particularly cold state, so that it can also be used, for example, as a cooling medium.

[0094] In the combustion chamber device 10, it is provided that the cooling of the inner shell 14 takes place according to the principle of effusion cooling or transpiration cooling. For this purpose, a fluid, for example a cooling medium, which flows through the flow region 54 of the flow channel 42, is guided at least partially into the structural material 32 of the inner shell 14. This will be explained in detail below. In this way, the fluid reaches the inner side 34 of the inner shell 14 facing the combustion chamber 12 via an inner region 60 of the inner shell 14. This allows a homogeneous cooling film to be created on the inner side 34. This allows the combustion chamber device to be cooled effectively and homogeneously.

[0095] Transpiration cooling essentially follows the same principle as the effusion cooling described above. Transpiration cooling also involves a phase change of the cooling fluid. This phase change can be achieved by selecting the appropriate cooling medium. This further increases the effectiveness of the cooling process.

[0096] A fluid-impermeable inner shell layer 62 is arranged on the side 58 of the inner shell 14, which defines the interior space 56 of the flow channel 42. The inner shell layer 62 is applied, for example, to the structural material 32 of the inner shell 14. It is applied, for example, to the structural material 32 by a galvanic process. The inner shell layer 62 is, in particular, bonded to the structural material 32.

[0097] The inner shell layer 62 is not necessarily designed as a continuous layer on the outer side 36 of the inner shell 14. In the region of intermediate elements 52, the inner shell layer 62 may have interruptions, for example, between adjacent flow channels 42.

[0098] The inner jacket layer 62 is fluid-impermeable. The inner jacket layer 62 has, in particular, high thermal conductivity.

[0099] The inner jacket layer 62 is made, for example, of a metallic material such as a copper electroplating.

[0100] The fluid-impermeable inner jacket layer 62 prevents penetration of fluid from the flow region 54 of the flow channel 42 into the structural material 32 of the inner jacket 14.

[0101] The fluid-impermeable inner shell layer 62 has a plurality of openings 64 through which a fluid-effective connection can be established between the flow region 54 of the flow channel 42 and the structural material 32 of the inner shell 14. The fluid-impermeable inner shell layer 62 is interrupted at one opening 64.

[0102] The flow region 64 of the flow channel 42 directly adjoins the structural material 32 of the inner shell 14 at the opening 64. At the opening 64, the interior space 56 of the flow channel 42 is delimited by the structural material 32 of the inner shell 14. In this way, fluid flow from the interior space 56 of the flow channel 42 through the opening 64 into the structural material 32 of the inner shell 14 is enabled.

[0103] The openings 64 are formed, for example, as elongated interruptions in the inner cladding layer 62. A main extension direction of the elongated interruptions is oriented, in particular, parallel to the longitudinal extension direction 44 of the flow channel 42.

[0104] The openings 64 are formed on the inner shell layer 62, for example, in the region of the intermediate element 52. The intermediate element 52 has, for example, a recess 66 within which the openings 64 are formed on the inner shell layer 62. The recess 66 runs, in particular, parallel to the longitudinal direction 44 of the flow channel 42.

[0105] A plurality of openings 64 are formed, for example, over the entire length of the flow channel 42 at the indentation 66. Adjacent openings 64 are spaced parallel to the longitudinal direction 44 of the flow channel 42.

[0106] For example, within a flow channel 42, two opposing indentations 66a, 66b are formed, at which the inner jacket layer 62 has the openings 64. The opposing indentations 66a, 66b are formed in particular on opposing intermediate elements 52a, 52b.

[0107] In the illustrated embodiment of the combustion chamber device 10, a baffle device 68 is provided, by means of which the fluid effectiveness of the connection between the at least one flow channel 42 and the structural material 32 of the inner casing 14 can be controlled and / or regulated.

[0108] For this purpose, the aperture device 68 comprises a plurality of aperture elements 70, wherein one aperture element 70 is arranged between an opening 64 of the fluid-impermeable inner jacket layer 62 and the flow region 54 of the at least one flow channel 42. The aperture element 70 is positioned between the opening 64 and the interior space 56 of the flow channel 42.

[0109] The aperture element 70 has a fluid-impermeable region 72 and at least one inflow channel 74 for fluid.

[0110] The inflow channel 74 is guided through the fluid-impermeable region 72 of the diaphragm element 70. The inflow channel 74 has an inlet opening 76 facing the interior space 56 of the flow channel 42 and an outlet opening 78 opposite the inlet opening 76. The outlet opening 78 faces the opening 64 of the inner jacket layer 62. The outlet opening 78 is formed, for example, on a side of the diaphragm element 70 facing the opening 64.

[0111] For example, an inflow channel 74 of the diaphragm element 70 is associated with an opening 64 of the inner cladding layer 62. The diaphragm element is arranged with the inflow channel 74 so as to be displaceable relative to the opening 64. In particular, the outlet opening 78 of the inflow channel 74 is displaceable relative to the opening 64 of the inner cladding layer 62.

[0112] In this way, a fluidic connection between the flow region 54 of the flow channel 42 and the structural material 32 of the inner casing 14 can be established or interrupted via the orifice device 64. The fluidic effectiveness of the connection can be continuously regulated, in particular, by means of the orifice device 68. This will be explained in more detail below.

[0113] In the embodiment shown (see Fig. 2), the aperture device 68 comprises a plurality of aperture elements 70 positioned on a holding element 80. For example, one aperture element 70 is assigned to each opening 64. For the sake of clarity and clarity, only one holding element 80 with aperture elements 70 is shown in the figures shown.

[0114] Various panel elements 70 are each integrally connected to one another on the holding element 80 and / or are formed integrally on the holding element 80.

[0115] In particular, a distance 81a between adjacent openings 64 of the inner jacket layer 62 corresponds to a distance 81b between adjacent inflow channels 74 of the aperture device 68.

[0116] The holding element 80 is, for example, rod-shaped, wherein a main extension direction is oriented parallel to the longitudinal extension direction 44 of the flow channel 42.

[0117] The holding element 80 is arranged displaceably within the flow channel 42. The holding element 80 is displaceable, for example, parallel to the longitudinal direction 44. In this way, the inflow channels 74 of the diaphragm elements 70, which are positioned on the holding element 80, are also displaceable parallel to the longitudinal direction 44. As a result, in the illustrated embodiment, the inflow channels 74 are displaceable relative to the openings 64 of the inner jacket layer 62.

[0118] For the displaceable mounting of the aperture elements 70, the flow channel 42 has, for example, a guide element 82. The guide element 82 is formed, for example, by the indentation 66 of the flow channel 42 or encompasses the indentation 66.

[0119] A diaphragm element 70 of the diaphragm device 68 has, in particular, a counter element 84 corresponding to the guide element 82, which can be inserted and / or snapped into the guide element 82. For this purpose, the counter element 84 comprises, for example, a bulge 86, which can be inserted into the recess 66 positioned on the intermediate element 52.

[0120] By means of the counter element 84, the aperture element 70 is displaceably mounted within the guide element 82 parallel to the longitudinal direction 44. In the illustrated embodiment, movement of the aperture element 70 in directions transverse to the longitudinal direction 44 of the flow channel 42 is at least partially blocked by a positive fit.

[0121] In one embodiment, it is provided that opposing holding elements 80 are connected within a flow channel 42 via a connecting element 88 (cf. Fig. 3) are connected to each other.

[0122] For example, a holding element 80a is connected to an opposite holding element 80b via the guide element 82. The holding element 80a is arranged at the indentation 66a of the flow channel 42, and the holding element 80b is arranged at the indentation 66b.

[0123] The connecting element 88 is, for example, integrally connected to the holding elements 80a, 80b.

[0124] The connecting element 88 is positioned, for example, facing the inner side 38 of the outer shell 16.

[0125] The connecting element 88 is designed to be resilient, for example, with the retaining elements 80a, 80b, so that the retaining elements 80a, 80b can be moved toward each other by overcoming a spring force. This allows the retaining elements 80a, 80b to be clamped, for example, between the indentations 66a, 66b of the flow channel 42.

[0126] In one embodiment, it is provided that the aperture device 68 has an adjusting element 90, by means of which one or more holding elements 80 can be displaced (cf. Fig. 4). To improve clarity, Fig. 4 only one holding element 80 of the aperture device 68 is shown.

[0127] The adjustment element 90 is arranged, for example, at one end 92 of the holding element 80. The adjustment element 90 is, for example, integrally connected to the holding element 80.

[0128] In particular, all retaining elements 80 of the diaphragm device 68 are arranged on the adjustment element 90. As a result, in particular, a displacement of all diaphragm elements 70 of the diaphragm device 68 relative to the openings 64 of the inner jacket layer 62 can be achieved by means of the adjustment element 90. In the illustrated embodiment, the diaphragm elements 70 of the diaphragm device 68 can be displaced parallel to the longitudinal direction 80 of the flow channel 42 by means of the adjustment element 90.

[0129] The adjusting element 90 is, for example, circular in shape.

[0130] The adjusting element 90 is arranged, for example, facing the first end 20 or the second end 26 of the combustion chamber 12.

[0131] By means of the aperture device 68, for example, an inflow of fluid from the flow region 54 of the flow channel 42 into the structural material 32 of the inner shell 14 can be controlled and / or regulated, in particular in a continuously variable manner.

[0132] Various states of the aperture device 68 are shown as examples in the Fig. 5 and Fig. 6 and labeled I to V. In Fig. 5 shows a top view of the holding element 80. Fig. Figure 6 shows a sectional view of states I to V along the line 2-2 according to Fig. 5.

[0133] In state I, the fluidic connection between the flow region 54 of the flow channel 42 and the structural material 32 of the inner casing 14 is interrupted. The outlet openings 78 of the inflow channels 74 of the diaphragm elements 70 each face the fluid-impermeable inner casing layer 62. The fluid-impermeable regions 72 of the diaphragm elements 70 face the openings 64 of the inner casing layer 62. In state I, therefore, no fluid can pass from the flow region 54 into the structural material 32.

[0134] State V is the opposite of state I. In state V, the fluidic connection between the flow region 54 and the structural material 32 is fully established. The outlet openings 78 of the inflow channels 74 face the openings 64 of the inner cladding layer 62.

[0135] Fluid from the flow region 54 enters the inflow channel 74 via the inlet opening 76 and leaves the inflow channel 74 via the outlet opening 78 into the opening 64 of the inner jacket layer 62. From there, the fluid can flow directly into the structural material 32.

[0136] States II to IV are corresponding intermediate states between state I (no fluid flow) and state V (maximum fluid flow). Between states II and IV, the fluid effectiveness of the connection between the flow region 54 and the structural material 32 increases. The amount of fluid that can flow from the flow region 54 into the structural material 32 depends on the overlap of the outlet openings 78 of the inflow channels 74 with the openings 64 of the inner cladding layer 62.

[0137] In the examples shown, in state II, the overlap of the outlet openings 78 with the openings 64 is small, so that only a small amount of fluid can flow from the flow region 54 into the structural material 32. In states III and IV, this overlap increases, so that an increasingly larger amount of fluid can flow from the flow region 54 into the structural material 32.

[0138] The setting of different states is carried out, for example, by moving the holding elements 80 within the flow channels 42. This is done, for example, by means of the adjustment element 90.

[0139] The intermediate states II to IV shown are merely examples. The degree of fluid effectiveness of the connection between the flow region 54 and the structural material 32 can be continuously controlled and / or regulated, in particular, via the aperture device 68.

[0140] In an alternative embodiment of a diaphragm device, which in Fig. 7 and designated there by 68', it is provided that aperture elements 70 are each arranged only in certain regions within the flow channel 42. The aperture device 68' is otherwise designed in the same way as the aperture device 68.

[0141] By arranging aperture elements 70 in specific regions, the control and / or regulation of the inflow of fluid from the flow region 54 of the flow channel 42 into the structural material 32 of the inner shell 14 can be limited to subregions of the combustion chamber device 10. This allows, for example, specific subregions of the combustion chamber device to be specifically cooled by means of effusion cooling or transpiration cooling.

[0142] In the Fig. In the embodiment shown in Figure 7, the aperture device 68' comprises a first group 94a of aperture elements 70, which are arranged in a region of a first end 96 of the flow channel 42. The first end 96 faces the first end 20 of the combustion chamber 12.

[0143] In the illustrated embodiment, the aperture device 68' has a second group 94b of aperture elements 70, which are positioned in a region of a second end 98 of the flow channel 42 opposite the first end 96. The second end 98 faces the second end 26 of the combustion chamber 12.

[0144] In one embodiment, an additional protective film 100 is arranged on the inner side 34 of the inner casing 14. The protective film 100 is, for example, a thermal protection film. This allows the thermal resistance of the inner casing 14 to be further increased.

[0145] Another embodiment of a combustion chamber device 10' is shown in the Fig. 9 and Fig. 10 and comprises an inner shell 14', which has a plurality of inner shell elements 108. The combustion chamber device 10' has basically the same functionality and is basically constructed in the same way as the combustion chamber device 10 described above. Identical or functionally equivalent elements of the combustion chamber devices 10 and 10' are provided with the same reference numerals. For these elements, reference is made to the above description of the combustion chamber device 10.

[0146] The inner jacket 14' is constructed, for example, from the inner jacket elements 108.

[0147] Different inner shell elements 108 are arranged one after the other along the longitudinal axis 46.

[0148] The inner shell elements 108 are, for example, ring-shaped and / or circular. The inner shell elements 108 surround and / or enclose the combustion chamber 12 and / or the longitudinal axis 46. The inner shell elements 108 are arranged, for example, rotationally symmetrically to the longitudinal axis 46. The respective centers of the inner shell elements 108 lie, for example, on the longitudinal axis 46.

[0149] The inner shell elements 108 are, for example, disc-shaped.

[0150] In the embodiment according to the Fig. 9 and Fig. 10, the inner shell 14' has inner shell elements 108a, 108b, 108c of three different types and / or types. The different inner shell elements 108a, 108b, 108c are arranged alternately along the longitudinal axis 46. The sequence of the inner shell elements is, for example, inner shell element 108a-inner shell element 108b-inner shell element 108c-inner shell element 108a-inner shell element 108b... etc.

[0151] The first-type inner jacket element 108a is made, for example, of a copper material or comprises a copper material. The second-type inner jacket element 108b is made, for example, of a chromium material or comprises a chromium material. The third-type inner jacket element 108c is made, for example, of a zirconium material or comprises a zirconium material.

[0152] The different inner jacket elements 108 each have, in particular, a different thermal conductivity and / or fluid permeability.

[0153] By means of the inner jacket elements 108, for example, heat dissipation can be realized parallel to the longitudinal axis 46. As a result, heat can be dissipated, for example, toward the first end 20 and / or the second end 26.

[0154] By means of the different inner jacket elements 108, the inner jacket 14' can be designed, for example, as a hybrid.

[0155] In this way, a combination of regenerative and transpiration cooling can be realized using the inner jacket 14'.

[0156] The combustion chamber device 10, 10' described above serves, for example, to drive a vehicle. The vehicle is, in particular, a missile. An embodiment of a missile comprising a combustion chamber device 10 or 10' is described in Fig. 7 and designated 102.

[0157] In the illustrated embodiment, the missile 102 is a rocket having an engine 104. The combustion chamber device 10, 10' is a component of this engine 104.

[0158] The combustion chamber device 10 functions as follows: A first and a second fluid are supplied to the combustion chamber 12, for example, by means of the injection device 18. In particular, a fuel-oxidizer mixture is introduced into the combustion chamber 12. Hydrogen, for example, is considered as the fuel. Oxygen, for example, is used as the oxidizer.

[0159] Due to the chemical reaction of the two fluids, in particular the fuel and the oxidizer, high pressures and temperatures arise in the combustion chamber 12 during operation of the combustion chamber device 10.

[0160] The exhaust gases, ie the reaction products of the fluids introduced into the combustion chamber 12, leave the combustion chamber device through the second end 26. Due to the expulsion of the exhaust gases from the combustion chamber, a thrust is generated counter to a main flow direction 106, which thrust can be used, for example, to propel a rocket.

[0161] The combustion chamber device 10 is cooled via the flow channels 42. For this purpose, a cooling medium, for example, flows through the flow channels 42. A suitable cooling medium, for example, is cold fuel, the temperature of which corresponds, for example, to the ambient temperature of the combustion chamber device 10. If cold fuel is used as the cooling medium, the flow channels 42 can also be used to supply the fuel to the injection device 18.

[0162] The combustion chamber device 10 is cooled by means of effusion cooling or transpiration cooling via the inner shell 14. For this purpose, an inflow of cooling medium from the flow region 54 of the flow channels 42 into the structural material 32 of the inner shell 14 is controlled and / or regulated, in particular continuously, via the aperture device 68. The aperture device 68 is controlled or regulated, for example, by displacing the adjusting element 90 in a direction particularly parallel to the longitudinal direction 44.

[0163] If the aperture device 68 is in state I, for example, the fluid supply from the flow region 54 into the structural material 32 of the inner shell 14 is interrupted, and no effusion or transpiration cooling occurs. However, if the aperture device 68 is in state V, for example, a maximum inflow of cooling medium into the structural material 32 of the inner shell 14 occurs. In state V, effusion or transpiration cooling therefore occurs at maximum intensity.

[0164] The ability to control and / or regulate the flow of the cooling medium from the flow region 54 into the structural material 32 of the inner shell 14 allows the cooling performance to be controlled and / or regulated. This enables optimal adaptation of the cooling performance to the respective temperature or power state of the combustion chamber device 10.

[0165] For example, the cooling capacity can be increased at a high temperature within the combustion chamber 12 and decreased at a low temperature within the combustion chamber 12. In this way, the efficiency of the combustion chamber device 10 is increased. List of reference symbols 10 Combustion chamber device 10' combustion chamber device 12 combustion chamber 14 inner jacket 14' inner jacket 16 Outer jacket 18 Injection device 20 first end 22 Entrance opening 24 Exit opening 26 second end 28 Longitudinal axis 30 radial direction 32 Structural material 34 Inside 36 Outside 38 Inside 40 Outside 42 flow channel 44 Longitudinal direction 46 Longitudinal axis 48 Circumferential direction 50 indentation 52 intermediate element 52a Intermediate element 52b Intermediate element 54 Flow area 56 Interior 58 page 60 interior 62 inner jacket layer 64 Opening 66 indentation 66a indentation 66b indentation 68 Aperture device 68' aperture device 70 aperture element 72 Area 74 inflow channel 76 Entrance opening 78 Exit opening 80 holding element 80a holding element 80b Holding element 81a distance 81b distance 82 guide element 84 Counter element 86 bulge 88 connecting element 90 Adjustment element 92 End 94a first group 94b second group 96 first end 98 second end 100 protective film 102 missiles 104 engine 106 Main flow direction 108 inner jacket element 108a Inner jacket element type 1 108b Inner jacket element type 2 108c inner jacket element type 3

Claims

[1] Combustion chamber device, comprising a combustion chamber (12) which is delimited by an inner shell (14; 14'), wherein the inner shell (14; 14') has a fluid-permeable structural material (32) and a fluid-impermeable inner shell layer (62), and wherein the inner shell (14; 14') comprises at least one flow channel (42) with a flow region (54) for fluid, characterized bythat the fluid-impermeable inner shell layer (62) is arranged on one side (58) of the structural material (32) of the inner shell (14; 14') and is integrally connected to the structural material (32), wherein the side (58) delimits the flow region (54) of the at least one flow channel (42) at least in some areas, that the fluid-impermeable inner shell layer (62) has at least one opening (64) by means of which a fluid-effective connection can be established between the flow region (54) of the at least one flow channel (42) and the fluid-permeable structural material (32) of the inner shell (14; 14'), that a diaphragm device (68; 68') with at least one diaphragm element (70) which is assigned to the at least one opening (64) is provided, by means of which the fluid effectiveness of the connection between the at least one flow channel (42) and the structural material (32) of the inner shell (14;14') is controllable and / or regulatable, and that the at least one diaphragm element (70) is arranged between the at least one opening (64) of the fluid-impermeable inner jacket layer (62) and the flow region (54) of the at least one flow channel (42), wherein the at least one diaphragm element (70) has a fluid-impermeable region (72) and at least one inflow channel (74) for fluid, which runs through the fluid-impermeable region (72); [2] Combustion chamber device according to claim 1, characterized by an outer shell (16) which surrounds an outer side (36) of the inner shell (14; 14') facing away from the combustion chamber (12). [3] Combustion chamber device according to claim 2, characterized by that the outer shell (16) comprises a fiber-reinforced plastic and in particular a carbon fiber-reinforced plastic. [4] Combustion chamber device according to one of claims 2 or 3, characterized bythat the flow region (54) of the at least one flow channel (42) is delimited at least in regions by an inner side (38) of the outer shell (16) facing the inner shell (14; 14'). [5] Combustion chamber device according to one of claims 2 to 4, characterized by that the at least one flow channel (42) is positioned between an outer side (36) of the inner shell (14; 14') facing the outer shell (16) and an inner side (38) of the outer shell (16) facing the inner shell (14; 14'). [6] Combustion chamber device according to one of the preceding claims, characterized by that the fluid-impermeable inner jacket layer (62) has a plurality of openings (64) which are spaced apart parallel to a longitudinal extension direction (44) of the at least one flow channel (42). [7] Combustion chamber device according to one of the preceding claims, characterized bythat the at least one inflow channel (74) of the at least one diaphragm element (70) is arranged displaceably relative to the at least one opening (64) of the fluid-impermeable inner jacket layer (62). [8] Combustion chamber device according to one of the preceding claims, characterized by that the diaphragm device (68; 68') has at least one holding element (80) on which one or more diaphragm elements (70) are arranged, and in particular that an adjusting element (90) is arranged on the at least one holding element (80), by means of which the at least one holding element (80) can be displaced with the diaphragm elements (70). [9] Combustion chamber device according to one of the preceding claims, characterized by that in each case an inflow channel (74) of the at least one diaphragm element (70) is assigned to an opening (64) of the fluid-impermeable inner jacket layer (62). [10] Combustion chamber device according to one of the preceding claims, characterized by that a distance (81a) between adjacent openings (64) of the fluid-impermeable inner jacket layer (62) corresponds to a distance (81b) between adjacent inflow channels of the diaphragm device (68; 68'). [11] Combustion chamber device according to one of the preceding claims, characterized by that the at least one flow channel (42) has at least one guide element (84), that the at least one diaphragm element (70) has a counter element (84) corresponding to the at least one guide element (82), and that the counter element (84) can be arranged, in particular displaceably, on the at least one guide element (82). [12] Combustion chamber device according to one of the preceding claims, characterized bythat the diaphragm device (68; 68') has a first group (94a) of diaphragm elements (70) which are arranged in a region of a first end (96) of the at least one flow channel (42), and that the diaphragm device (68; 68') has a second group (94b) of diaphragm elements (70) which are arranged in a region of a second end (98) of the at least one flow channel (42) opposite the first end (96). [13] Combustion chamber device according to one of the preceding claims, characterized by a plurality of flow channels (42) which are spaced apart from one another in a circumferential direction (48) of the inner shell (14; 14') lying transversely and in particular perpendicularly to a longitudinal axis (46) of the inner shell (14; 14'). [14] Combustion chamber device according to one of the preceding claims, characterized bythat the fluid-permeable structural material (32) of the inner shell (14; 14') comprises a fiber composite material and in particular a ceramic fiber composite material. [15] Combustion chamber device according to one of the preceding claims, characterized by that the inner shell (14; 14') has a plurality of inner shell elements (108; 108a; 108b; 108c) and / or that the inner shell (14; 14') is constructed from a plurality of inner shell elements (108; 108a; 108b; 108c), wherein the inner shell elements (108; 108a; 108b; 108c) are arranged successively parallel to a longitudinal axis (46) of the inner shell (14; 14'), and in particular that the inner shell elements (108; 108a; 108b; 108c) are each annular and / or circular. [16] Combustion chamber device according to claim 15, characterized bythat mutually adjacent inner casing elements (108; 108a; 108b; 108c) are each made of different materials or comprise different materials, and in particular that inner casing elements (108; 108a; 108b; 108c) of different types and / or different kinds are arranged alternately and / or alternately parallel to the longitudinal axis (46). [17] Vehicle, in particular missile (102), comprising a combustion chamber device according to one of claims 1 to 16. [18] Method for operating a combustion chamber device, comprising a combustion chamber (12) which is delimited by an inner casing (14; 14'), wherein the inner casing (14; 14') has a fluid-permeable structural material (32) and a fluid-impermeable inner casing layer (62) which is materially connected to the structural material (32), and wherein the inner casing (14; 14') comprises at least one flow channel (42) with a flow region (54) for fluid, wherein the fluid-impermeable inner casing layer (62) delimits the flow region (54) at least in regions in which a fluid flows through the at least one flow channel (42), the fluid from the at least one flow channel (42) at least partially through the at least one opening (64) into the structural material (32) of the inner casing (14;14'), and in which an inflow rate of the fluid from the at least one flow channel (42) into the structural material (32) of the inner casing (14; 14') is controlled and / or regulated by a diaphragm device (68; 68') with at least one diaphragm element (70) which is assigned to the at least one opening (64) and is arranged between the at least one opening (64) and the flow region (54);

Images