Combustion chamber with vibration-damping inner wall shape and method for producing a combustion chamber section

Description

[0001] The invention relates to a combustion chamber with a vibration-damping inner wall shape, as well as to a rocket engine with such a combustion chamber, a method for producing such a combustion chamber, and a computer-readable data carrier with instructions for carrying out the manufacturing method. In particular, the invention relates to a combustion chamber with a combustion chamber body having at least one section whose inner side is closer to a cross-sectional center of the combustion chamber body than another section of the combustion chamber body. Furthermore, a rocket engine with such a combustion chamber section, a layered construction method for producing such a combustion chamber, and a computer-readable data carrier with instructions for carrying out the layered construction method are described.

[0002] Combustion chambers of liquid rocket engines serve to efficiently burn the respective propellant pairing, consisting of oxidizer and fuel. For this purpose, the propellant components are fed into the chamber via a special injection system. Depending on the respective operating conditions, evaporation, mixing, chemical conversion, and the initial conversion into kinetic energy then take place in the chamber, the primary increase of which occurs in the subsonic and supersonic nozzle region. The flow in the combustion chamber is characterized by turbulent mixing. High combustion stability is desirable for reliable rocket engine operation.

[0003] Furthermore, cooling is necessary, particularly in the area of ​​the hot gas walls (inner walls of the combustion chamber and exhaust nozzle). For example, with regenerative cooling, the high heat development can be dampened via coolant channels in the hot gas walls through which at least one fuel component flows. Such coolant channels are shown, for example, in JP 2005-226586, US 2,476,185, and DE 570 511; in US 2,476,185, they are arranged spirally inside the combustion chamber.

[0004] Of the various combustion chamber shapes available, such as spherical, pear-shaped, conical, cylindrical, or even annular, the cylindrical combustion chamber configuration has emerged as the most popular. A cylindrical combustion chamber offers advantages, particularly in manufacturing. However, combustion chambers with a round cross-section are more susceptible to high-frequency vibrations, particularly transverse vibration modes, which correspond to the natural frequencies of these designs. These transverse vibrations, i.e. vibration propagation in the radial direction of the round combustion chamber, lead to additional energy release in the combustion chamber, resulting in overheating. Furthermore, significant pressure fluctuations are observed.

[0005] To counteract or prevent these vibrations, baffles (also known as "baffles" in technical terms) were arranged on the head plate (or injection plate) of the combustion chamber, as shown, for example, in JP 2005-226586. DE 10 2016 209 650 A1 proposes, instead of baffles, a certain number of coaxial injection elements on the head plate with a central sleeve body that protrudes further from the head plate into the interior of the combustion chamber than the other injection elements. The resulting axial staggering of the flame front in the combustion chamber reduces or prevents the formation and / or propagation of vibrations in a similar way to baffles.

[0006] Against this background, the present invention is based on the object of creating a combustion chamber with improved combustion stability.

[0007] This object is achieved by a combustion chamber having the features of claim 1, a rocket engine having the features of claim 10 and a method having the features of claim 11 and a corresponding data carrier with instructions according to claim 13.

[0008] According to a first aspect for a better understanding of the present disclosure, a combustion chamber for a rocket engine comprises a combustion chamber body enclosing a combustion chamber volume, and a nozzle portion tapering in the longitudinal direction of the combustion chamber and adjoining the combustion chamber body. The combustion chamber body is connected, for example, to an injection head on a side opposite the nozzle portion. The combustion chamber volume thus primarily serves for mixing and combustion of the propellant components.

[0009] The combustion chamber body has at least a first section and a second section, wherein an inner side of the at least one first section facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body than an inner side of the second section of the combustion chamber body. In other words, the inner side of the at least one first section is further inside the combustion chamber volume than the inner side of the second section and thus reduces the combustion chamber volume in this region of the combustion chamber body. The at least one first section can be any number of sections or regions of the combustion chamber body that locally delimit a smaller combustion chamber volume than in the region of the second section. The second section is all other sections or regions of the combustion chamber body that are not part of the at least one first section.The second section is also a uniformly shaped body which has a bulge (extending into the combustion chamber volume) on the inner side facing the combustion chamber volume in each of the regions of the at least one first section.

[0010] This special shape of the interior of the combustion chamber body divides the combustion chamber volume into different zones. This division counteracts the generation and / or propagation of vibrations, particularly transverse vibrations. Similar to baffles arranged on the injection head, the combustion chamber volume is divided, especially when viewed from a cross-section of the combustion chamber body, so that the propagation of vibrations is dampened or prevented. This increases the combustion stability of the rocket engine.

[0011] For example, several first sections of the combustion chamber body can be provided, each positioned where a baffle would normally be located. Due to the special shape of the combustion chamber body, the combustion chamber has no preferred natural frequencies, so the vibration problem is eliminated or at least greatly reduced.

[0012] In one embodiment, a distance between the inner side of the at least one first section and the cross-sectional center of the combustion chamber body can increase in the longitudinal direction and / or in the circumferential direction of the combustion chamber body from a minimum continuously up to a distance between the inner side of the second section of the combustion chamber body and the cross-sectional center of the combustion chamber body. For example, the inner side of the at least one first section can take on a round, three-dimensional shape. By avoiding sharp edges, such as those sometimes found in guide vanes, strong temperature gradients and / or vortices in the flow can be avoided, thus preventing areas with temperature peaks in the combustion chamber body.

[0013] The continuous surface profile of the inner side of at least one first section also makes it possible to provide a combustion chamber volume optimized for the flow of combustion gases. Thus, the advantages of guide vanes can be realized directly in the combustion chamber body, while also improving the flow in the longitudinal direction of the combustion chamber body (in the flow direction of the combustion gases). For example, turbulence can occur in the edge areas of guide vanes, which does not occur or only occurs to a very small extent in the combustion chamber body disclosed here.

[0014] The cross-sectional center of the combustion chamber body can correspond to a center of gravity of the cross-section of the combustion chamber body. The cross-section lies in a (cross-sectional) plane substantially perpendicular to a longitudinal direction of the combustion chamber, which corresponds to the flow direction of the combustion gases. The distance from the inside of the at least one first section or the second section to the cross-sectional center is measured in the cross-sectional plane. The minimum is thus the shortest distance between the cross-sectional center and any point on the intersection line of the inside of the first section with the plane.

[0015] In a further embodiment, the minimum distance between the inner side of the at least one first section and the cross-sectional center of the combustion chamber body can be arranged along a line extending in the longitudinal direction and / or circumferential direction of the combustion chamber body. When viewed in the circumferential direction, which preferably lies in the cross-sectional plane, the minimum is thus not limited to a single point, but can also represent a circular arc line with equal distances from the cross-sectional center. Viewed in the longitudinal direction of the combustion chamber body, the first section can have a point or a line in each of several adjacent cross-sectional planes that have a minimum distance from the cross-sectional center.The minimum can therefore be a single point, a line, or even a surface where the inner wall / inside of the first section is closest to the cross-sectional center, thus reducing the combustion chamber volume the most. This line or surface does not have to be straight, but can run in the longitudinal and / or circumferential direction of the combustion chamber body.

[0016] This special shape of the first section of the combustion chamber body allows the combustion chamber volume to be optimized for the flow of combustion gases. In particular, the size of the first section in the longitudinal and / or circumferential directions of the combustion chamber body can be adapted to the combustion gases used, thus facilitating the chemical reaction and ensuring optimal mixing. The average local Mach number in the respective area of ​​the combustion chamber volume can also be taken into account when selecting the size of the first section and / or the size of the minimum. Vibrations in the longitudinal direction of the combustion chamber body (longitudinal vibrations) can also be dampened or prevented.

[0017] In yet another embodiment, at least one cross-section of the combustion chamber body can be rotationally symmetrical, and the cross-sectional center of the combustion chamber body can be the pivot point of rotational symmetry. Rotationally symmetrical here does not mean the specific case of a circle, but rather (viewed in the circumferential direction) the arrangement of several first sections and the second section located between them, with each first section recurring in the cross-section at a fixed angle around the pivot point of rotational symmetry. Thus, an N-fold rotational symmetry exists, where N is the number of first sections in the cross-section.

[0018] In another embodiment, the at least one first section of the combustion chamber body can be located in the longitudinal direction of the combustion chamber body in a region of the combustion chamber body that forms a head-side end of the combustion chamber body. The head-side end of the combustion chamber body is the end at which the injection head is connected to the combustion chamber. Thus, the arrangement of the at least one first section roughly corresponds to the position of guide vanes in conventional combustion chambers.

[0019] Alternatively or additionally, the at least one first section of the combustion chamber body can be located in the longitudinal direction of the combustion chamber body in a region of the combustion chamber body that forms a nozzle-side end of the combustion chamber body adjacent to the nozzle part. The nozzle-side end of the combustion chamber body is opposite the head-side end (viewed in the longitudinal direction of the combustion chamber body).

[0020] Alternatively or additionally, the at least one first section of the combustion chamber body can be located in the longitudinal direction of the combustion chamber body in a region of the combustion chamber body that forms a central region between the head-side end and the nozzle-side end of the combustion chamber body. Thus, the head-side end and the nozzle-side end of the combustion chamber body can assume a conventional shape (in particular a conventional cross-section) of a combustion chamber, while, viewed in the longitudinal direction of the combustion chamber body, constrictions of the combustion chamber volume are arranged in the central region by the at least one first section.

[0021] Further alternatively, the at least one first section of the combustion chamber body can extend in the longitudinal direction of the combustion chamber body over the entire combustion chamber body.

[0022] In a further design variant, the combustion chamber body can comprise an even number of first sections. This results in a particularly symmetrical and therefore stable combustion chamber body.

[0023] Alternatively or additionally, at least two first sections can be arranged in the combustion chamber body in the longitudinal direction of the combustion chamber body. The two first sections or the plurality of first sections can be arranged along a straight line that runs parallel to the longitudinal direction of the combustion chamber body. Alternatively, the plurality of first sections can also be arranged along a curved path, wherein the curved path runs on a virtual inner side of a base body of the combustion chamber body, which is defined by the second section.

[0024] In yet another embodiment, the combustion chamber may further comprise a cylindrical section extending in the longitudinal direction of the combustion chamber. In particular, the inside of the combustion chamber has a cylindrical shape in the cylindrical section. In other words, part of the combustion chamber may be manufactured in a conventional design (cylindrical), while, viewed in the longitudinal direction of the combustion chamber, only a specific part is manufactured by the combustion chamber body with the special shape defined by the at least one first section and the second section. For example, the cylindrical section may be adjacent to the nozzle part, thereby achieving efficient flow through the combustion chamber.

[0025] Alternatively or additionally, the combustion chamber may also include a nozzle supersonic segment extending longitudinally from the nozzle section. Such a nozzle supersonic segment is also found in conventional combustion chambers or thrust chambers.

[0026] Furthermore, according to the present invention, a plurality of coolant channels extending in the longitudinal direction of the combustion chamber body are arranged in the at least one first section and the second section of the combustion chamber body. The coolant channels are arranged as close as possible to the inside of the combustion chamber body in order to sufficiently cool the inside of the combustion chamber body, which is heated by the combustion gases. One of the fuel components can be passed through the coolant channels, which advantageously heats it for subsequent combustion.

[0027] In a further embodiment, each of the coolant channels in the combustion chamber body can have a coolant outlet. In this case, in the circumferential direction along a cross-section of the combustion chamber body, a further coolant outlet of an adjacent coolant channel can be arranged in the combustion chamber body next to one of the coolant outlets. In other words, the coolant outlets (the coolant channel outlets) form a chain along the circumference of the cross-section of the combustion chamber body. These outlets can open into a circumferential collecting space (manifold).

[0028] Furthermore, the combustion chamber body according to the present invention has a substantially uniform wall thickness throughout. In other words, the outer side or outer wall of the combustion chamber body forms a depression or indentation in the region of the at least one first section.

[0029] In another design variant, the combustion chamber body can be formed in one piece. "Integral" here means that at least most parts of the combustion chamber body, such as the inner wall, outer wall, and the webs separating the coolant channels between the inner wall and outer wall, are made of a continuous material. For example, the combustion chamber body or the entire combustion chamber can be manufactured using a layered construction process (also known as 3D printing or ALM - additive layer manufacturing). It is also possible to manufacture only parts of the combustion chamber body using a layered construction process and build them onto a section of the combustion chamber body manufactured in another way. Different materials can also be used in the layered construction process. For example, a more heat-resistant material can be used on the inside of the combustion chamber body than on the outside of the combustion chamber body.

[0030] According to a second aspect for a better understanding of the present disclosure, a rocket engine comprises a combustion chamber according to the first aspect or one of the design variants described therein.

[0031] According to a third aspect for a better understanding of the present disclosure, a method for manufacturing a combustion chamber according to the first aspect or one of its embodiment variants comprises a layered construction process. If coolant channels are present in the combustion chamber body, no material can be joined by the layered construction process at positions where the coolant channels of the combustion chamber body are located.

[0032] According to a fourth aspect for better understanding of the present disclosure, a computer-readable data carrier comprises instructions that, when executed on a processor, cause a machine to perform the layered construction method according to the third aspect. These instructions may be CAD data or similar data that describe or define the shape of the combustion chamber or combustion chamber body according to the first aspect, in particular such that a machine can form the combustion chamber section and / or the combustion chamber layer by layer.

[0033] The present disclosure is therefore not limited to the individual embodiments and variants in the described order or to a specific combination of the aspects and embodiment variants. Preferred embodiments of the invention will now be explained in more detail with reference to the attached schematic drawings, wherein Figure 1 schematically shows a perspective view of a combustion chamber; Figure 2 schematically shows a section of a combustion chamber body; Figure 3 schematically shows another section of a combustion chamber body; Figure 4 schematically shows a perspective view and a plan view of a combustion chamber; and Figure 5 schematically shows a perspective view and a plan view of a differently designed combustion chamber.

[0034] Figure 1 shows schematically a perspective view of a combustion chamber 100, which can be used, for example, in a rocket engine 10. The nozzle of the rocket engine 10 is in Figure 1 The combustion chamber 100, as shown in Figure 1The combustion chamber 120, shown in simplified form, comprises a combustion chamber body 120 enclosing a combustion chamber volume in which a large part of the mixing and combustion of the fuel components takes place. Downstream (in the flow direction of the combustion gases), the combustion chamber body 120 is adjoined by an optional combustion chamber section 110 and a subsonic nozzle section 112 in which the combustion gases are accelerated, followed by a supersonic nozzle segment 114.

[0035] In the area of ​​the nozzle supersonic segment 114, there is a connection 131 for coolant, which opens into a distribution ring 132 (also called a distribution manifold). The distribution ring 132 extends in the circumferential direction and forms a continuous annular volume. Coolant channels 130 open into this volume, or viewed in the direction of coolant flow (in Figure 1 shown by a dashed arrow) a plurality of coolant channels 130 begin in the distribution ring 132.

[0036] The coolant channels 130 are also arranged in the combustion chamber section 110 and the combustion chamber body 120, so that the coolant channels 130 of the nozzle supersonic segment 114 extend to the head end of the combustion chamber 100 (left end of the combustion chamber 100 in Figure 1 ). For clarity, only some of the coolant channels 130 are shown in Figure 1 shown exposed and only in an area spaced from the distribution ring 132. Of course, the coolant channels 130 extend in the area of ​​the nozzle supersonic segment 114 to the distribution ring 132.

[0037] A flange 125 is provided at the upstream end of the combustion chamber 100, as viewed in the direction of combustion gas flow. This flange 125 serves to connect the combustion chamber head (not shown). As shown in the detailed view in the Figures 2 and 3As shown, a plurality of coolant outlets 138 are located in the region of the flange 125, with each coolant channel 130 in the combustion chamber body 120 having such a coolant outlet 138. The coolant outlets 138 are arranged adjacent to one another in the circumferential direction along a cross-section of the combustion chamber body 120. The coolant outlets 138 can open into a distribution ring or collecting ring (not shown), which is provided at the other end of the combustion chamber 100, corresponding to the distribution ring 132.

[0038] The Figure 1 The combustion chamber section 110, shown cylindrically, can take on any cross-sectional shape that serves the efficient combustion of the fuel components. The combustion chamber section 110 is in Figure 1In particular, it is shown to illustrate a possible base body of the combustion chamber 100. This possible (virtual) base body of the combustion chamber 100 can also be found, at least in some areas, in the combustion chamber body 120.

[0039] Deviating from this basic body, the combustion chamber body 120 has at least a first section 121 and a second section 122. These two sections 121, 122 are shown in the detailed views of the Figures 2 and 3 clearly visible. An inner side of the at least one first section 121 facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body 120 than an inner side of the second section 122 of the combustion chamber body 120. In Figure 1 A combustion chamber body 120 with a total of six first sections 121 is shown. However, the number of first sections 121 can be chosen arbitrarily and can be either an even or odd number.

[0040] The Figure 1 The first sections 121 shown have a minimum distance M (minimum) from a cross-sectional center of the combustion chamber body 120. From this minimum M, the distance of the inside of the at least one first section 121 from the cross-sectional center of the combustion chamber body 120 changes continuously in the longitudinal direction and in the circumferential direction up to a distance of the inside of the second section 122 of the combustion chamber body 120 from the cross-sectional center. This distance of the inside to the cross-sectional center therefore increases continuously. As a result, the combustion chamber volume is divided into specific regions, with the first sections 121 representing a constriction. These constricted regions fulfill a similar function to guide vanes arranged on an injection head (not shown). However, the continuous course of the inside of the combustion chamber body 120 creates a flow-optimized surface.

[0041] Depending on the type of fuel, vibrations with different parameters can occur in the combustion chamber volume. To counteract these vibrations, the at least one first region 121 and the second region 122 are dimensioned in the longitudinal and / or circumferential direction of the combustion chamber body 120 such that the vibrations that would otherwise occur are dampened or suppressed.

[0042] The coolant channels 130 are guided through both the first sections 121 and the second section 122, viewed in the longitudinal direction of the combustion chamber body 120. Due to the change in the inner side between the first region 121 and the second region 122, the coolant channels 130 can also have different cross-sectional shapes. For example, the coolant channels 130 in the first region 121 can be wider when viewed in the circumferential direction in order to accommodate the increasing surface area (also viewed in the circumferential direction). It is advantageous if the cross-sectional area of ​​each coolant channel 130 extends from the nozzle-side end (right in Figure 1 ) up to the head end (left in Figure 1) is not or only slightly changed.

[0043] The combustion chamber body 120 (or the entire combustion chamber 100) can be manufactured quite quickly and easily using a layered construction process (3D printing or ALM). The material forming at least one first section 121 and the second section 122 can be applied layer by layer, and the entire combustion chamber 100 can be manufactured layer by layer. All coolant channels 130 can be manufactured by omitting a material deposit, thus creating a cavity.

[0044] The layered construction process allows the cavities forming the coolant channels 130 to be manufactured in a simple manner. This allows even complex structures to be realized, particularly in the transition area between the combustion chamber section 110 and the combustion chamber body 120 and / or in the area of ​​continuous variation of the interior of the combustion chamber body 120 in the region of the at least one first section 121 and second section 122, which would not be possible with other manufacturing processes. Thus, combustion chamber bodies 120 that are easy to cool and flow-optimized can be produced in a simple process, with particular attention being paid to good vibration damping, regardless of a changing course of the coolant channels 130.

[0045] The Figures 4 and 5 show schematic perspective views and top views of two combustion chambers 100. In the example according to Figure 4The first sections 121 of the combustion chamber body 120 are provided at the head end of the combustion chamber 100. The minimum M of the distance A1 of the inner side of the first section 121 to the cross-sectional center Z is located, for example, at the head end of the combustion chamber 100. The distance (starting from A1) increases continuously along the longitudinal direction and circumferential direction of the combustion chamber body 120 until it reaches the distance A2 of the inner side of the second section 122 to the cross-sectional center Z. Of course, the minimum M can be present not only at a point, but also along a line (for example, running in the longitudinal direction) or on a surface.

[0046] In the supervision of the Figures 4 and 5(viewed in the longitudinal direction of the respective combustion chamber 100) it can also be seen that the combustion chamber volume tapers in the region of the nozzle section 112, in particular the cross section of the combustion chamber 100 tapers down to the nozzle section diameter D.

[0047] In the example according to Figure 5 First sections 121 are also provided, which cause a reduction of the combustion chamber volume. However, these first sections 121 are located in a central region viewed in the longitudinal direction of the combustion chamber 100, i.e. between the head end (left in Figure 5 ) and the nozzle-side end (right in Figure 5) of the combustion chamber body 120. The remaining area of ​​the combustion chamber body 120 surrounding the first section 121 represents a basic body in the form of the second section 122. In the head-side and nozzle-side areas, one can therefore also speak of a combustion chamber section 110 which has the shape of a conventional combustion chamber (here a cylindrical combustion chamber shape).

[0048] The Figures 4 and 5 The arrangements of the at least one first section 121 shown are merely exemplary. While in Figure 5the first sections 121 are arranged along a ring, it is of course possible for a plurality of first sections 121 to be arranged along two rings in the combustion chamber body 120. In this case, the first sections 121 along a ring, viewed in the circumferential direction of the combustion chamber body 120, can be arranged rotated relative to the first sections 121 of another ring. It is also conceivable that the first sections do not extend along the longitudinal direction of the combustion chamber body 120, as is the case, for example, in the Figures 4 and 5 Rather, the first sections 121 can also run along a curved line. This allows, for example, a rotational component to be incorporated into the flow of the combustion gases or even reduced.

[0049] Furthermore, the outside of the combustion chamber body 120 follows as shown in the Figures 4 and 5shown the course of the inside in both the first sections 121 and the second sections 122. As a result, the wall of the combustion chamber body 120 has predominantly the same thickness.

[0050] Finally, in each of the embodiments described here, not only an indentation in the form of the at least one first section 121 can be present, but also a bulge 123 (only in Figure 5 (shown). Furthermore, the bulge 123 can also replace the second section 122. Such one or more bulges enable the same Mach number to be present in the region of the combustion chamber body 120 and the combustion chamber section 110.

Claims

1. A combustion chamber (100) for a rocket engine (10), the combustion chamber (100) comprising: - a combustion chamber body (120) enclosing a combustion chamber volume; and - a nozzle part (112) that tapers in the longitudinal direction of the combustion chamber (100) and that adjoins the combustion chamber body (120), wherein the combustion chamber body (120) has at least one first section (121) and a second section (122), characterized in that the combustion chamber body (120) has a substantially constant wall thickness, the second section (122) forms at least part of a cylindrical base body of the combustion chamber body (120), an inner side of the at least one first section (121) facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body (120) than an inner side of the second section (122) of the combustion chamber body (120), in the at least one first section (121) and the second section (122) of the combustion chamber body (120) a plurality of coolant channels (130) is arranged, which extend in the longitudinal direction of the combustion chamber body (120) and follow the course of the inside of the at least one first section (121) and the second section (122), and each coolant channel (130) that follows the course of the inside of one of the at least one first section (121) also passes through the second section (122) in the longitudinal direction of the combustion chamber body (120).

2. The combustion chamber (100) according to claim 1, wherein a distance (A1) of the inside of the at least one first section (121) from the cross-sectional center (Z) of the combustion chamber body (120) continuously increases in the longitudinal direction and / or in the circumferential direction of the combustion chamber body (120) from a minimum (M) up to a distance (A2) of the inside of the second section (122) of the combustion chamber body (120) from the cross-sectional center (Z) of the combustion chamber body (120).

3. The combustion chamber (100) according to claim 2, wherein the minimum (M) of the distance (A1) of the inside of the at least one first section (121) from the center (Z) of the cross section of the combustion chamber body (120) is arranged along a line extending in the longitudinal direction and / or in the circumferential direction of the combustion chamber body (120).

4. The combustion chamber (100) according to one of claims 1 to 3, wherein at least one cross section of the combustion chamber body (120) is rotationally symmetrical and the cross-sectional center (Z) of the combustion chamber body (120) is the center of rotation of the rotational symmetry.

5. The combustion chamber (100) according to one of claims 1 to 4, wherein the at least one first section (121) of the combustion chamber body (120) is located in the longitudinal direction of the combustion chamber body (120) in a region of the combustion chamber body (120) which forms a head-side end of the combustion chamber body (120) or which forms a nozzle-side end of the combustion chamber body (120) adjacent to the nozzle part (112) or which forms a central region between the head-side end and the nozzle-side end of the combustion chamber body (120), or wherein the at least one first section (121) of the combustion chamber body (120) extends in the longitudinal direction of the combustion chamber body (120) over the entire combustion chamber body (120).

6. The combustion chamber (100) according to one of claims 1 to 5, wherein the combustion chamber body (120) comprises an even number of first sections (121), and / or wherein at least two first sections (121) are arranged in the combustion chamber body (120) in the longitudinal direction of the combustion chamber body (120).

7. The combustion chamber (100) according to one of claims 1 to 6, further comprising: - a cylindrical section (110) extending in the longitudinal direction of the combustion chamber (100).

8. The combustion chamber (100) according to one of claims 1 to 7, further comprising: - a supersonic nozzle segment (114) adjoining the nozzle part (112) in the longitudinal direction of the combustion chamber (100).

9. The combustion chamber (100) according to claim 1, wherein each of the coolant channels (130) in the combustion chamber body (120) has a coolant outlet (138), and wherein, in the circumferential direction along a cross-section of the combustion chamber body (120), an additional coolant outlet (138) of an adjacent coolant channel (130) in the combustion chamber body (120) is arranged next to one of the coolant outlets (138).

10. A rocket engine (10) having a combustion chamber (100) according to one of claims 1 to 9.

11. A method for producing a combustion chamber (100) according to one of claims 1 to 9, the combustion chamber (100) being built up by a layering manufacturing method.

12. The method according to claim 11 for producing a combustion chamber (100) according to claim 8 or 9, wherein no material is joined by the layering manufacturing method at positions where the coolant channels (130) of the combustion chamber body (120) are located.

13. A computer-readable storage medium comprising instructions that, when executed on a processor, cause a machine to perform the layering manufacturing method according to claim 11 or 12.