Abstract:
The invention relates to a sealing arrangement  15 , a guide vane arrangement, and a turbomachine  11  with such a sealing arrangement  15 , wherein the sealing arrangement  15  is designed for a guide vane ring  60  of a turbomachine  11 , wherein the sealing arrangement  15  comprises a thin-walled annular structure  80  that is substantially closed on all sides, and wherein the annular structure  80  delimits an annular interior space  105 , wherein a hollow cell structure  109 , which is designed so as to mechanically support the annular structure  80 , is provided in the annular interior space  105.

Description:
BACKGROUND OF THE INVENTION 
     The invention relates to a sealing arrangement for a turbomachine, a guide vane arrangement, and a turbomachine with such a sealing arrangement, which comprises a thin-walled annular structure that is substantially closed on all sides, and wherein the annular structure delimits an annular interior space. 
     Known from DE 10 2006 004 090 A1 is a sealing arrangement of a gas turbine with a guide vane and an inner shroud arranged at the radially inner-lying end of the guide vane, wherein a sealing element is an integral component of the inner shroud and serves to seal a radially inner-lying gap between the sealing arrangement and the gas turbine rotor. 
     It is further known that sealing arrangements at guide vanes can be designed at least in part in an annular form and comprise a thin-walled annular structure, in order to reduce any gas flow through various gaps in the region of the sealing arrangement. In this case, the annular structure delimits an annular interior space. Usually, these designs must be composed of a plurality of parts that are assembled. Also, the gas present in the annular interior space can be induced to create vortexing through a movement of the annular structure, said vortexing causing additional friction in the gas turbine. 
     BRIEF SUMMARY OF THE INVENTION 
     It is the object of the invention to provide an improved sealing arrangement for a turbomachine, a guide vane arrangement, and a turbomachine with such a sealing arrangement. 
     This object is achieved by the embodiments of the sealing arrangement the present invention. 
     In accordance with the invention, it was known that an improved sealing arrangement can be provided in that the sealing arrangement comprises a thin-walled annular structure that is substantially closed on all sides and wherein the annular structure delimits an annular interior space. Furthermore, a hollow cell structure, which is designed so as to mechanically support the annular structure, is provided in the annular interior space. 
     In this way, it is ensured that, within the annular interior space, any vortexing due to a gas present there is prevented. Furthermore, the hollow cell structure supports the annular structure on the inside, so that the annular structure can be designed to be especially thin-walled, and the weight of the sealing arrangement is overall reduced. 
     It has been found to be especially advantageous when the hollow cell structure comprises a foam structure, preferably an open-pored foam, in particular preferably an open-pored metallic foam, as material. The open-pored nature of the foam has the advantage that, when the sealing arrangement is heated, which can usually occur up to 600° C., a pressure equalization occurs within the foam between the pores of the foam. In this way, it is prevented that, when the sealing arrangement is heated, the foam is subjected to unnecessarily high material loads due to expansion of the gas present in the foam. 
     In another embodiment, the hollow cell structure comprises a support structure, with the support structure having a honeycomb design. This configuration of the sealing arrangement is particularly rigid in one direction. 
     In another embodiment, the hollow cell structure has at least two webs and at least three nodal points, with the webs being linked at the nodal points to the annular structure and/or with the webs being linked among one another to form a framework. This design makes possible a particularly simple and load-adapted design of the sealing arrangement. 
     In another embodiment, the annular structure has at least one passage opening, which connects the annular interior space to the surroundings of the sealing arrangement, with the at least one passage opening being designed for pressure equalization of the annular interior space with its surroundings. If the guide vane ring, as explained above, is heated, then the gas present in the pores of the hollow cell structure flows through the hollow cell structure and ultimately through the passage opening, so that the gas contained in the hollow cell structure can be reliably discharged from the annular interior space, and hence any potential destruction of the annular structure resulting from an overpressure in the foam can be prevented. 
     In another embodiment, an additional passage opening for pressure equalization of the annular interior space is provided, with the passage opening and the additional passage opening being arranged on the same side of the annular structure. In this way, it is prevented that a gas flow occurs through both passage openings and the foam structure arranged in between them. 
     In another embodiment, the annular structure comprises at least one uptake on an outer peripheral surface, said uptake being designed to accommodate at least one annular member of the guide vane ring. In this way, it is possible to fasten the sealing arrangement to the guide vane ring in a simple manner. 
     In another embodiment, the uptake has a first contact surface arranged on the upstream side and a second contact surface arranged on the downstream side, with the annular structure having a first wall thickness at the first contact surface and a second wall thickness at the second contact surface, with the first wall thickness differing from the second wall thickness. In this way, the force acting on the annular structure, resulting, for example, from the higher first pressure applied on the upstream side in comparison to a second pressure applied to the annular structure on the downstream side, can be reliably diverted into the annular structure via the first contact surface. At the same time, the sealing arrangement can be designed to be especially lightweight. Thus, in a turbine, the first wall thickness can be designed to be greater than the second wall thickness, while in a compressor, the second wall thickness can be designed to be greater than the first wall thickness, so as to provide a load-adapted sealing arrangement. 
     It is especially advantageous when a radial inner-lying sealing structure is provided at the annular structure and preferably has a honeycomb or foam-like design, with the hollow cell structure comprising a first mean pore size and the sealing structure comprising a second mean pore size, with the first mean pore size of the hollow cell structure being smaller than the second mean pore size of the sealing structure. 
     In another embodiment, the annular structure and the hollow cell structure and preferably the sealing structure are designed to be one-piece and uniform in material. In this way, it is possible to provide an especially rigid sealing arrangement. 
     In another embodiment, at least the annular structure and the hollow cell structure and advantageously the sealing structure are fabricated jointly by means of a laser powder deposition welding process or by means of a selective laser melting process or by means of a selective laser sintering process. Each of the processes mentioned makes possible an especially fine and precisely defined fabrication of the hollow cell structure while simultaneously bonding it to the annular structure, so that individual walls of the hollow cell structure merge directly into the annular structure and hence an especially rigid sealing arrangement can be provided. Furthermore, fluctuations in the fabrication of the hollow cell structure during conventional foaming of the foam material, for example, can be reliably prevented, because each individual pore or cell of the hollow cell structure and also of the annular structure can be specified in a defined manner by means of the selective laser melting process or the selective laser sintering process or the laser powder deposition welding process. 
     It has also been found to be especially advantageous when the hollow cell structure and the annular structure comprise an essentially identical material, with the material comprising at least one of the following constituents: steel, aluminum, ceramic, titanium, nickel, cobalt. 
     The invention will also be accomplished, however, by a guide vane arrangement as described below. 
     In accordance with the invention, it was recognized that an improved guide vane arrangement can be provided in that the guide vane arrangement comprises a guide vane ring and a sealing arrangement, with the sealing arrangement being arranged at the guide vane ring in a radially outer-lying and/or radially inner-lying manner, with the sealing arrangement being designed as explained above. 
     In this way, it is possible to reduce any leakage-gas flow that occurs lateral to the guide vane ring without passing the guide vane ring, so that the gas flow diverted through the guide vane ring can be increased. 
     The invention is also accomplished, however, by a turbomachine having the features described below. 
     In accordance with the invention, it was recognized that an improved turbomachine can be provided in that the turbomachine comprises at least one rotor disk arranged so as to rotate and at least one stator, with the rotor disk comprising at least one rotor blade and the stator comprising at least one guide vane ring, with the at least one rotor blade being assigned to the at least one guide vane ring, and with at least one sealing arrangement being provided at the at least one guide vane ring on the radially outer side and/or on the radial inner side, said sealing arrangement being designed as explained above. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The invention will be explained in detail below on the basis of figures. Shown are: 
         FIG. 1 , a longitudinal section through a turbine of a gas turbine; 
         FIG. 2 , a cutout of the longitudinal section shown in  FIG. 1  with a sealing arrangement; 
         FIG. 3 , a longitudinal section through the sealing arrangement shown in  FIG. 2 ; 
         FIG. 4 , a cutout of a cross section through the sealing arrangement shown in  FIG. 3 ; 
         FIG. 5 , a longitudinal section through a variant of the sealing arrangements shown in  FIG. 2 ; 
         FIG. 6 , a longitudinal section through another embodiment of the sealing arrangement shown in  FIG. 2 ; and 
         FIG. 7 , a longitudinal section through another embodiment of the sealing arrangement shown in  FIG. 2 . 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       FIG. 1  shows a longitudinal section through a turbine  10  and  FIG. 2  shows a cutout of the longitudinal section shown in  FIG. 1  through the turbine  10  with a sealing arrangement  15 .  FIG. 3  shows a longitudinal section through the sealing arrangement  15  shown in  FIG. 2 .  FIG. 4  shows a cutout of a cross section through the sealing arrangement  15  shown in  FIG. 3  along a sectional plane B-B shown in  FIG. 3 . In the following, identical components will be identified with the same reference numbers. Furthermore,  FIGS. 1 to 4  will be explained jointly so as to facilitate understanding. 
     An exhaust gas  20  coming from a combustion chamber, which is not illustrated, flows from left to right in  FIGS. 1 and 2  through the turbine  10  of an aircraft gas turbine  11 . In this case, the turbine  10  comprises a drum  25 , which is mounted so as to rotate about an axis of rotation  30 . The turbine  10  comprises a plurality of stages  35 ,  40 ,  45 , with a stator  50  being arranged in front of a rotor disk  55  for each stage  35 ,  40 ,  45 . Each stator  50  comprises at least one guide vane ring  60  with at least one guide vane  61 , which is designed so as to divert the exhaust gas flow  20  in the peripheral direction. The rotor disk  55  comprises at least one rotor blade  65  arranged at the drum  25  on the radially outer side. The rotor blade  65  is driven by the exhaust gas flow  20 , so that the drum  25  is put into rotation. On the radially inner side, the rotor blade  65  is joined to the drum  25  via a blade root  70 . In order to prevent the radially rotating rotor blade  65  from striking against the guide vane ring  60  when the turbine  10  is in operation, the rotor blade  65  is arranged at a distance from the guide vane ring  60  via a gap  75 . A first pressure p 1  is usually applied in front of the stator  50 . After the stator  50 , on a downstream side of the stator  50 , a second pressure p 2  is applied. The first pressure p 1  is greater than the second pressure p 2  in this case. In order to circumvent any pressure equalization at the stator  50  on the radially inner side, the stator  50  or the guide vane ring  60  has the sealing arrangement  15  arranged on the radially inner side with respect to the guide vane  61 . 
     The sealing arrangement  15  comprises an annular structure  80 , which has a rectangular, preferably a trapezoidal, cross section. However, other cross-sectional shapes of different design are also conceivable. On the radially inner side, a sealing structure  85  is provided at the annular structure  80 , in which sealing elements  90 , which are arranged at the drum  25 , engage. The sealing structure  85 , together with the sealing elements  90 , prevent any leakage flow of the exhaust gas flow  20  due to the pressure difference between the first pressure p 1  and the second pressure p 2  axially between the sealing arrangement  15  and the drum  25 . In this case, the sealing structure  85  preferably comprises a honeycomb structure or foam-like structure. The sealing structure  85  has a first sealing segment  95 , arranged on the upstream side, and a second sealing segment  100 , arranged on the downstream side with respect to the first sealing segment  95 . The sealing segments  95 ,  100  are arranged with a radially inward displacement with respect to each other in this case, with one sealing element  90  engaging in each sealing segment  95 ,  100 . As a result of the radial displacement of the sealing segments  95 ,  100 , the sealing structure  85  can be adapted to the geometric shape of the drum  25  or to the arrangement of the sealing elements  90  at the drum  25 . In  FIGS. 1 and 2 , the adaptation of the sealing segments  95 ,  100  is chosen such that the first sealing segment  95  is arranged in a radially inner-lying manner with respect to the second sealing segment  100 . It is also conceivable for the second sealing segment  100  to be arranged in a radially inner-lying manner with respect to the first sealing segment  95 . Alternatively, it is conceivable that both sealing segments  95 ,  100  are arranged radially at the same level. 
     The annular structure  80  encloses an annular interior space  105 , which, in this embodiment, is completely filled with a hollow cell structure  109 , which is designed as a foam structure  110 . The foam structure  110  has individual cells or pores  130 . Alternatively, it is also conceivable that the annular interior space  105  is filled only partially, preferably, however, to at least 50%, ideally to at least 80%, with the foam structure  110 . In this case, it is advantageous that, when there is only partial filling of the annular interior space  105  with the foam structure  110 , the latter is arranged preferably on the radially outer side. 
     The foam structure  110  comprises, as material, an open-pored foam, preferably an open-pored metallic foam. Advantageously, the annular structure  105  or the foam structure  110  has at least one of the following materials: steel, aluminum, ceramic, titanium. The foam structure  110  further has a first mean pore size. A mean pore size is understood to refer to an average value of the size of individual pores  130  of the foam structure  110  or of the sealing structure  85 , determined over a majority of pores  130 . The sealing structure  85  has a second mean pore size, with the first mean pore size of the foam structure  110  being smaller than the second mean pore size of the sealing structure  85 . In this way, it is ensured that the sealing elements  90  can engage in the sealing structure  85  with little friction. Furthermore, it is ensured at the same time by the smaller mean first pore size of the foam structure  110  that the sealing arrangement  15  is designed to be especially rigid due to the foam structure  110 . 
     The annular structure  80  encloses the foam structure  110  essentially completely and seals the foam structure  110  against the surroundings of the sealing arrangement  15 , especially against the exhaust gas flow  20 , essentially completely. In order to make possible a pressure equalization between the annular interior space  105  and the surroundings of the sealing arrangement  15 , the annular structure  80  has a first passage opening  115 . In this case, the first passage opening  115  is arranged at a lateral surface  120  of the annular structure  80  on the downstream side. The first passage opening  115  connects the surroundings of the sealing arrangement  15  to the annular interior space  105  of the annular structure  80 . Under the operating conditions, the sealing arrangement  15  of the turbine  10  is heated to up to 600° C. Owing to the open-pored design of the foam structure  110 , the gases entrapped in the foam structure  110  can be exchanged or flow between individual pores  130  of the foam structure  110  and flow out of the annular structure  80  via the first passage opening  115  when there is a higher pressure in the annular interior space  105 . In order to facilitate the flow of the gases trapped in the individual pores  130  out of the annular structure  80 , a second passage opening  135  is provided on the radially outer side with respect to the first passage opening  115 . The second passage opening  135  is arranged on the same lateral surface  120  as the first passage opening  115  in this case so as to prevent any gas from flowing through the foam structure  110  owing to the pressure difference between the first pressure p 1  and the second pressure p 2  in the axial direction. Obviously, the passage openings  115 ,  135  can also be arranged on another lateral surface of the annular structure  105 . It is also possible to dispense with the passage openings  115 ,  135 . 
     The sealing arrangement  15  further comprises an uptake  145  at an outer circumferential surface  140 , which is arranged on the annular structure  105  lying opposite the sealing structure  85 . The uptake  145  extends in this case essentially perpendicular to the axis of rotation  30  from the outer peripheral surface  140  toward the sealing structure  85 . In this case, the uptake  145  is open radially outward. In the embodiment, a plurality of uptakes  145  are provided, which are arranged in the peripheral direction at a regular spacing with respect to one another on the outer peripheral surface  140 . The radial extension of the uptake  145  is chosen such that an uptake end  150  of the uptake  145  is arranged at a radial distance to the sealing structure  85 , so that both the annular structure  80  and the foam structure  110  are arranged between the uptake end  150  and the sealing structure  85 . In this way, it is ensured that a pressure equalization can also occur for the pores  130  of the foam structure  110  that are arranged on the left side of the uptake  145  via the passage openings  115 ,  135  arranged on the right side of the uptake  145 . Furthermore, the arrangement of the annular structure  80  and the foam structure  110  between the uptake end  150  and the sealing structure  85  provides for a rigid design of the sealing arrangement  15 , so that it is prevented that, when the turbine  10  is in operation, the sealing arrangement  15  can be induced to undergo undesired vibration. The uptake  145  comprises a first uptake surface  151  arranged on the left side and a second uptake surface  155  arranged on the right on the downstream side, with the first uptake surface  151  or the second uptake surface  155  being oriented essentially perpendicular to the axis of rotation  30  of the turbine  10 . Obviously, an angled arrangement of the contact surfaces  151 ,  155  with respect to the axis of rotation  30  is also conceivable. The first contact surface  151  is designed to be parallel to the second contact surface  155 . The annular structure  80  has a first overhang  160  on the upstream side at the outer peripheral surface  140  on the radially outer side and a second overhang  165  arranged on the downstream side with respect to the first overhang  160 . As a result of the overhangs  160 ,  165 , the uptake side  145  is extended radially outward and the contact surfaces  150 ,  155  are enlarged. 
     The stator  50  has an annular member  170  on the radially inner side, which comprises a plurality of spokes  175 . The spokes  175  are designed in this case as sliding elements, which, at their end sides  180 ,  185  each rest against the contact surfaces  151 ,  155  assigned to them. In this way, it is ensured that, when the guide vane ring  60  is heated, any change in the diameter of the annular member  170  can be compensated by sliding of the end sides  180 ,  185  of the spokes  175  in the uptake  145  at the respective contact surfaces  151 ,  155 . In their design, the spoke  175  and the corresponding uptake  145  are adapted to each other such that any twisting of the sealing arrangement  15  at the annular member  170  is prevented and, at the same time, a guiding and fixixng in place of the sealing arrangement  15  at the annular member  170  is ensured. 
     On account of the elevated first pressure p 1  on the upstream side of the sealing arrangement  15  in comparison to the second pressure p 2  prevailing on the downstream side on the right in  FIG. 3 , the sealing arrangement  15  is pressed against a first end side  180  of the spoke  175 , which faces the first contact surface  151 , with a pressing force F due to the positive pressure difference between the first pressure p 1  and the second pressure p 2  via the first contact surface  151 . In this case, the annular structure  80  has a first wall thickness d 1  at the first contact surface  151  that is greater than a second wall thickness d 2  of the annular structure  80  at the second contact surface  155 . The thicker first wall thickness d 1  of the annular structure  80  continues further in the first overhang  160 , so as, also via the first overhang  160 , to be able to introduce an increased pressing force F on the spokes  175  via the first contact surface  151 . The second contact surface  155  rests against a second end side  185  of the spoke  175  and serves to guide the annular structure  80  at the annular member  170 . On account of the smaller forces applied to the second contact surface  155 , the second overhang  165  can be made smaller or more delicate in its design than the first overhang  160 . This embodiment makes possible a weight-optimized and hence lower-cost design of the sealing arrangement  15 . If the sealing arrangement  15  is employed in a compressor, instead of in a turbine  10 , it is advantageous, on account of the higher pressure p 2  on the downstream side in comparison to the first pressure p 1 , to design the second wall thickness d 2  at the second contact surface  155  to be greater than the first wall thickness d 1  at the first contact surface  151 . Obviously, it is also conceivable that the two wall thicknesses d 1  and d 2  can be designed to be equal in value. 
     In the embodiment, the uptake  145  extends in sections in the peripheral direction. Obviously, it is also conceivable that the uptake  145  is designed to extend around the entire periphery. In the embodiment, the annular structure  80  has a rectangular or a trapezoidal cross section. Obviously, cross sections different from the cross sections shown in  FIGS. 1 to 3  are also conceivable. It would also be conceivable that, for example, the annular structure  80  comprises a circular or elliptical or polygonal cross section. Furthermore, it is noted that the overhangs  160 ,  165  can obviously be designed to be radially shorter or longer. The overhangs  160 ,  165  can also be dispensed with, given an adequate depth of the uptake  145  in the sealing arrangement  15 . 
     As a result of the above-described design of the sealing arrangement  15  and as a result of the filling of the annular interior space  105  with the foam structure  110 , it is possible to provide an especially rigid sealing arrangement  15 . Furthermore, the filling of the annular interior space  105  can result in the prevention of any vortexing or an increased friction of gases in the annular interior space  105  of the annular structure  80 . This applies particularly in the case when the annular interior space  105  is completely filled with the foam structure  110 . 
     It is further noted that, in  FIGS. 1 and 2 , the application of the sealing arrangement  15  in the turbine  10  is shown in a third stage  45 . Obviously, the described sealing arrangement  15  can also be employed in the other stages  35 ,  40 . The turbine  10  is intended to serve, by way of example, for the application of the sealing arrangement  15  in a compressor of the gas turbine  11  as well. 
       FIG. 5  shows a longitudinal section through a variant of the sealing arrangement  15  shown in  FIG. 2 . The sealing arrangement  15  is substantially identical to the sealing arrangement  15  explained above. In departure from it, however, the first mean pore size of the foam structure  110  is greater than the mean pore size of the foam structure  110  shown in  FIG. 3 . In this way, it is possible to provide an especially lightweight and rapidly fabricated sealing arrangement  15 . 
       FIG. 6  shows a longitudinal section through another embodiment of the sealing arrangement shown in  FIG. 2 . The sealing arrangement  15  is substantially identical to the embodiments explained in  FIGS. 1 to 5 ; unlike these, the hollow cell structure  109  comprises a support structure  190 , which has a plurality of honeycombs  195 . The honeycombs  195  are designed as hexagons in the embodiment. Obviously, other shapes are also conceivable. In this embodiment, the individual honeycombs  195  of the support structure  190  extend radially outward and thus have the same orientation as the honeycombs  200  of the sealing structure  85 . Obviously, a different orientation—for example, in the axial direction—is also conceivable. 
       FIG. 7  shows a longitudinal section through another embodiment of the sealing arrangement  15  shown in  FIG. 2 . The sealing arrangement  15  is substantially identical to the embodiments explained in  FIGS. 1 to 6 ; unlike these, the support structure  190  is designed as a framework. In this case, the support structure  190  comprises a plurality of webs  205 . The webs  205  are linked to one another at nodal points  210 . Furthermore, a portion of the webs  205 , which are adjacent to the annular structure  80 , are linked both to other webs  205  and to the annular structure  80  at the nodal points  210 . As a result, it is possible to provide an especially rigid hollow cell structure  109 . 
     It is noted that the diffrent embodiments of the hollow cell structure  109  shown in  Figures 1 to 7  can also be combined with one another in order to adapt the rigidity of the sealing arrangement  15  to be appropriate to the load. 
     In the embodiments shown, the annular structure  80  is designed to be rectilinear between the hollow cell structure  109  and the sealing structure  85 . Obviously, it is also conceivable that the annular structure  80  is integrated in the sealing structure  85  or foam structure  110  and follows, for example, the the course of a wall of the sealing structure  85  and/or of the foam structure  110  and thus is designed, for example to be corrugated or partially honeycombed. Also conceivable is a continuous transition from the hollow cell structure  109  to the sealing structure  85 . 
     It is especially advantageous when the sealing arrangement  15  is fabricated by means of a selective laser melting process or by means of a selective laser sintering process or by means of a laser powder deposition welding process. This kind of fabrication has the advantage that, defined by means of a laser, the individual pores  130  of the foam structure  110  can be fixed in their pore size. In this way, any scattering in terms of the porosity or the size of the pores  130  is avoided. It is also possible for the annular structure  80  to be defined so as to be particularly thin-walled in design, because, through bonding of the foam material  110  to the annular structure  80 , a unit constructed of one piece and uniform in material can be provided, which is designed to be especially rigid and free of material boundaries, so that any abrasion at such a material boundary between the foam material  110  and the annular structure  80  can be avoided because the boundary does not exist. 
     Furthermore, it is possible by means of the named fabrication process to dispense with additional mounting steps for fabrication of the sealing arrangement  15 . Beyond this, it is possible, on account of the defined creation of the individual pores  130  of the foam structure  110  by means of the selective laser melting process or by means of a selective laser sintering process or by means of the laser powder deposition welding process to provide large-volume sealing arrangements  15 , so that larger cavities can be filled on the radially inner side between the drum  25  and the guide vane ring  60  as well. 
     In addition, the large-volume design of the sealing arrangement  15  can also make possible an improved shielding of the radially inner-lying region between the guide vane ring  60  and the drum  25 . Parasitic secondary flows are also largely prevented. Furthermore, by way of the selective laser melting process or selective laser sintering process or the laser powder deposition welding process, the sealing arrangement  15  can be dimensioned in a load-adapted manner and additional joining elements, such as screws or rivets, which are subject to critical design in the fabrication of high-temperature components, can be avoided. It is especially advantageous, moreover, when the passage openings  115 ,  135  are suitable not only for pressure equalization in terms of their arrangement and design, but also for removal of excess material from the selective laser melting/sintering process or laser powder deposition welding process. 
     The generative manufacture of the sealing arrangement  15  by means of one of the above-mentioned processes and the above-described design of the sealing arrangement  15  makes it possible, furthermore, to freely shape the annular structure  80  in terms of its contours and to adjust it freely to the geometry of the components adjacent to the sealing arrangement  15 . The above-described sealing arrangements  15  have minimal, load-adapted wall thicknesses with avoidance of doublings in design and without the use of junctions, so that an especially weight-optimized sealing arrangement  15  can be provided. In addition, there is less friction due to smaller cavities and smooth outer walls.