Combustion chamber assembly with a flow guiding device comprising a wall element

Abstract

A combustion chamber assembly for an engine includes a wall element fixed to a combustion chamber structure and a chamber between the wall element and the structure, the chamber being supplied with air through impingement-cooling openings in the structure and connected to the combustion space by film-cooling openings in the wall element. Two cooling-air holes formed in the structure generate a cooling-air flow toward the combustion space and past the wall element. The wall element has a flow guide device for generating at least one scavenging-air flow directed between the two cooling-air holes. A sum of flow cross sections of film-cooling openings in the wall element and of the flow guide device yields a larger area than a sum of flow cross sections of all wall element impingement-cooling openings via which air is guided through the structure into the chamber and to the rear side of the wall element.

Claims

1. A combustion chamber assembly for an engine, comprising: a wall element which has an outer side facing toward a combustion space and has a rear side facing away from the combustion space, the wall element including film-cooling holes therethrough, a combustion chamber structure to which the wall element is fixed and toward which the rear side of the wall element faces, the combustion chamber structure including impingement-cooling openings therethrough, a chamber between the wall element and a portion of the combustion chamber structure, air being supplied through the impingement-cooling openings into the chamber and to the rear side of the wall element, the chamber being connected to the combustion space by the film-cooling holes in the wall element, cooling-air holes formed in the combustion chamber structure for generating a cooling-air flow in a direction of the combustion space and past the wall element, wherein the wall element includes a flow guide device having a flow cross section for generating a scavenging-air flow directed between two of the cooling-air holes in the combustion chamber structure, wherein a sum of flow cross sections of all of the film-cooling holes and of the flow guide device on the wall element has a larger area than a sum of flow cross sections of all of the impingement-cooling openings for the wall element.

2. The combustion chamber assembly according to claim 1, wherein the larger area is at least 1.2 times greater than the sum of the flow cross sections of all of the impingement-cooling holes for the wall element.

3. The combustion chamber assembly according to claim 2, wherein the larger area is 1.2 to 4 times greater than the sum of the flow cross sections of all of the impingement-cooling holes for the wall element.

4. The combustion chamber assembly according to claim 3, wherein the larger area is 1.8 to 3 times greater than the sum of the flow cross sections of all of the impingement-cooling holes for the wall element.

5. The combustion chamber assembly according to claim 1, and further comprising a web, wherein the flow guide device includes at least one blow-off opening in the web which projects on the rear side of the wall element and which borders the chamber.

6. The combustion chamber assembly according to claim 5, wherein the at least one blow-off opening defines a flow passage which points in a direction of an intermediate space formed between the two cooling-air holes, which are adjacent in a circumferential direction, in the combustion chamber structure.

7. The combustion chamber assembly according to claim 6, wherein the at least one blow-off opening includes a plurality of blow-off openings which each defines a flow passage, and at least two of the flow passages are oriented differently.

8. The combustion chamber assembly according to claim 5, wherein the web extends along at least two edges of the wall element.

9. The combustion chamber assembly according to claim 8, wherein the wall element includes a first wall element and a second wall element and the at least one blow-off opening includes a plurality of blow-off openings, and a radially extending first edge of the first wall element faces a radially extending second edge of the second wall element which is adjacent in a circumferential direction, and, each of the mutually facing first and second edges, includes one of the plurality of blow-off openings oriented in the circumferential direction and such that a respective scavenging-air flow generated by each the plurality of blow-off openings do not intersect.

10. The combustion chamber assembly according to claim 1, wherein the wall element has four sides, each of the four sides having a respective edge, which define an outer contour of the wall element, and the flow guide device includes first and second flow guide devices provided at two gap regions at which two of the four sides converge.

11. The combustion chamber assembly according to claim 1, wherein the wall element includes a plurality of wall elements which are situated adjacent to one another along a circumferential direction and, the flow guide device includes a plurality of flow guide devices, with each of the plurality of wall elements including one of the plurality of flow guide devices.

12. The combustion chamber assembly according to claim 1, wherein the wall element includes first and second wall elements and the first wall element incudes the flow guide device, the flow guide device generating the scavenging-air flow in a direction of the second wall element which is situated adjacent to the first wall element in a circumferential direction.

13. The combustion chamber assembly according to claim 12, wherein the flow guide device generates the scavenging-air flow in a direction of a corner of the second wall element.

14. The combustion chamber assembly according to claim 1, wherein the wall element includes first and second wall elements adjacent to each other in a circumferential direction, the first and second wall elements being separated from one another by a gap, and the scavenging-air flow is directed into the gap.

15. The combustion chamber assembly according to claim 14, wherein the flow guide device includes first and second flow guide devices, with the first and second wall elements respectively including the first and second flow guide devices, with scavenging-air flows of the first and second flow guide device 1) being directed toward interstices between the two cooling-air holes situated in the gap and 2) not intersecting.

16. The combustion chamber assembly according to claim 1, wherein the wall element includes first and second wall elements positioned adjacent one another, wherein the flow guide device includes a first flow guide device and a second flow guide device, wherein the first wall element includes the first flow guide device and the first flow guide device includes a first blow-off opening defining a first flow passage, a second blow-off opening defining a second flow passage and a third blow-off opening defining a third flow passage, wherein the scavenging air flow includes first, second and third scavenging-air flows, wherein the first flow passage extends along a radial direction, the second flow passage extends along a circumferential direction, and the third flow passage extends so as to be inclined with respect to the radial direction and inclined with respect to the circumferential direction, the first, the second, and the third flow passages comprising, respectively, the first, the second, and the third scavenging air flows, wherein the second wall element includes the second flow device producing an adjacent scavenging air flow, wherein at least one chosen from the second and the third scavenging-air flows is arranged so as to not intersect the adjacent scavenging air flow or the cooling-air flow.

17. The combustion chamber assembly according to claim 16, wherein the first, the second, and the third scavenging-air flows intersect neither the adjacent scavenging-air flow nor the cooling-air flow.

18. The combustion chamber assembly according to claim 1, wherein the wall element includes first and second wall elements mounted on the combustion chamber structure, wherein an angle of 150 to 210 degrees is provided between the first and the second wall elements on the outer sides of the first and second wall elements, the cooling-air holes being situated between the first and the second wall elements in a circumferential direction to form the cooling-air flow on one of the first and second wall elements, and the scavenging-air flow is arranged in a direction of an interstice between the two cooling-air holes.

19. The combustion chamber assembly according to claim 1, wherein the wall element includes first and second wall elements, the first wall element being formed as a heat shield with a through hole for a fuel nozzle and being mounted onto a base plate of the combustion chamber structure, and the second wall element being formed as a combustion chamber shingle and mounted onto a combustion chamber wall of the combustion chamber structure, wherein an angle of 70 to 120 degrees is provided between the first and the second wall elements on the outer sides of the first and the second wall elements, the cooling-air holes being situated between the first and the second wall elements in a circumferential direction to form the cooling-air flow on the second wall element, the scavenging-air flow being arranged in a direction of an interstice between the two cooling-air holes.

20. A gas turbine engine having the combustion chamber assembly according to claim 1.

Description

(1) In the figures:

(2) FIG. 1 shows, in a detail, a longitudinal section through a combustion chamber assembly with a focus on a connecting point of a base plate of the combustion chamber assembly and a heat shield mounted spaced apart from said base plate and on a combustion chamber wall of the combustion chamber, illustrating an orientation of scavenging-air jets between air jets which emerge from the base plate and later form a cooling film;

(3) FIG. 2 shows, in a detail and with a view directed toward the rear side, the heat shield with several flow guide devices on the edge of the heat shield for the purposes of generating scavenging-air jets which are directed into interstices between those air jets which emerge from the base plate and later form the cooling film;

(4) FIG. 3 shows a schematic developed view along the flow path of the air jets from the base plate of the combustion chamber assembly which later form the cooling film, illustrating scavenging-air jets which have been generated by the heat shield and which fill the interstice between the component webs between cooling-air openings in the base plate and the air jets formed from these;

(5) FIG. 4 shows, with a view directed onto the respective rear side, multiple heat shields, which are situated adjacent to one another along a circumferential direction, of a proposed combustion chamber assembly, wherein the flow guide devices are provided with scavenging-air openings for generating the scavenging-air jets, which are in each case directed in particular onto the component web between two film-cooling openings in the base plate of the combustion chamber assembly;

(6) FIG. 5 shows, in a detail and with a view along the gap between two heat shields in a radial direction, an arrangement of two scavenging-air openings in adjacent heat shields, which generate scavenging-air jets with different spacings to the base plate and are directed toward the same interstice between the cooling-air openings for forming a cooling film;

(7) FIG. 6A shows a longitudinal section through the entire combustion chamber, in this case with wall elements not only on the base plate around the burner but also on the combustion chamber wall, in order that no part of a combustion chamber structure of the combustion chamber is directly exposed to the hot gas in the combustion space of the combustion chamber;

(8) FIG. 6B shows an enlarged detail of FIG. 6A showing details of an interstice between wall elements situated upstream and the wall elements situated downstream with interposed holes in the combustion chamber structure for the purposes of forming a cooling film on the wall element situated downstream;

(9) FIG. 7A shows an engine in which a combustion chamber assembly corresponding to FIGS. 1 to 6B is used;

(10) FIG. 7B shows, in a detail and on an enlarged scale, the combustion chamber of the engine of FIG. 7A.

(11) FIG. 7A illustrates, schematically and in a sectional illustration, a (gas turbine) engine T, in which the individual engine components are arranged one behind the other along an axis of rotation or central axis M, and the engine T is formed as a turbofan engine. At an inlet or intake E of the engine T, air is drawn in along an inlet direction by means of a fan F. This fan F, which is arranged in a fan casing FC, is driven by means of a rotor shaft S, which is set in rotation by a turbine TT of the engine T. Here, the turbine TT adjoins a compressor V, which comprises for example a low-pressure compressor 111 and a high-pressure compressor 112, and possibly also a medium-pressure compressor. The fan F firstly feeds air in a primary air flow F1 to the compressor V and secondly, in order to generate the thrust, feeds air in a secondary air flow F2 to a secondary flow passage or bypass passage B. Here, the bypass passage B runs around a core engine, which comprises the compressor V and the turbine TT and comprises a primary flow passage for the air fed to the core engine by the fan F.

(12) The air conveyed into the primary flow passage by means of the compressor V passes into a combustion chamber portion BKA of the core engine, in which the drive energy for driving the turbine TT is generated. For this purpose, the turbine TT has a high-pressure turbine 113, a medium-pressure turbine 114 and a low-pressure turbine 115. Here, the energy released during the combustion is used by the turbine TT to drive the rotor shaft S and thus the fan F in order to generate the required thrust by means of the air conveyed into the bypass passage B. Both the air from the bypass passage B and the exhaust gases from the primary flow passage of the core engine flow out via an outlet A at the end of the engine T. In this arrangement, the outlet A generally has a thrust nozzle with a centrally arranged outlet cone C.

(13) FIG. 7B shows a longitudinal section through the combustion chamber portion BKA of the engine T. It is possible from this to see in particular an (annular) combustion chamber BK of the engine T. For the injection of fuel or of a air-fuel mixture into a combustion space 21 of the combustion chamber BK, a nozzle assembly is provided. Said nozzle assembly comprises a combustion chamber ring, on which multiple fuel nozzles 77 are arranged along a circular line around the central axis M. Here, on the combustion chamber ring, there are provided the nozzle outlet openings of the respective fuel nozzles 77 which are situated within the combustion chamber BK. Here, each fuel nozzle 77 comprises a flange by means of which a fuel nozzle 77 is screwed to an outer casing 72 of the combustion chamber portion BKA. The illustrated combustion chamber BK is in this case for example a (fully) annular combustion chamber such as is used in gas turbine engines. Via an arm 58 and a flange 59, an outer combustion chamber wall of the combustion chamber BK is connected to the outer casing 72.

(14) FIG. 1 shows the combustion chamber BK in longitudinal section with a design variant of a proposed combustion chamber assembly. Here, in the intended installed state, a wall element 5, in FIG. 1 in the form of a heat shield, lies with an edge-side web 7 on a front-side base plate 2 of the combustion chamber BK. The base plate 2 is connected to a cover 1 situated upstream and to a combustion chamber wall 4 situated downstream, and thus forms a combustion chamber structure 22, which encases the combustion space 21, of the combustion chamber BK.

(15) The wall element 5 has an outer side facing toward the combustion space 21 and has a rear side which is averted from the combustion space 21 and which thus faces toward the base plate 2. A (flow) chamber 6 is formed between the wall element 5 and the base plate 2 of the combustion chamber structure 22, which (flow) chamber is supplied with air through impingement-cooling openings 23 in the combustion chamber structure 22 and is connected to the combustion space 21 by film-cooling openings 24 in the wall element 5. Also formed in the combustion chamber structure 22, in this case on the base plate 2, are cooling-air holes 3 which are provided for generating a cooling-air flow which flows in the direction of the combustion space 21 and past the wall element 5.

(16) For the generation of at least one scavenging-air flow 12 which is directed between two of the cooling-air holes 3, a flow guide device 10 for scavenging air is provided in the wall element 5. Said flow guide device 10 has multiple blow-off openings 10.1, 10.2 and 10.3 which are formed on the web 7 projecting on the edge side and which define in each case one flow passage. Here, a radially extending blow-off opening 10.1 extends along an axis 11 and is oriented such that a scavenging-air jet 12.1 (see FIG. 2), formed in said blow-out opening, of the scavenging-air flow 12 flows over a component web 20 between two cooling-air holes 3 in the combustion chamber structure 22 (see FIG. 3). In this way, during the operation of the engine T, a region of the combustion chamber structure 22 on the combustion chamber wall 4 outside the cooling-air openings 3 is freed from hot gas, that is to say is scavenged. Here, jet edges 13, 13.1 of a generated scavenging-air jet of a scavenging-air flow 12 adjoin cooling-air jets 14 from the cooling-air openings 3, and are ideally tangent to these.

(17) Provision is made here whereby the sum of the flow cross sections of the film-cooling holes 24 and of the flow guide device 10 (more specifically of the blow-off openings and of the flow passages 10.1, 10.2 and 10.3, defined thereby, of the flow guide device 10) in the wall element 5 yields an area which is at least 1.2 times greater than the sum of the flow cross sections of all impingement-cooling holes 23 in the region of a wall element 5. In this way, the flow guide device 10 of the wall element 5 is fed with a much lower pressure level from the chamber 6 than the cooling-air holes 3 in the base plate 2, because the greater part of the overall pressure drop across the combination of base plate 2 and wall element 5 occurs across the base plate 2, but the same overall pressure drop occurs across the cooling-air holes 3 alone.

(18) FIG. 2 shows, with a view directed onto a rear side, the wall element 5 with stud bolts 17 (or similar fastening elements) which are provided thereon and by means of which the wall element 5, with the edge-side encircling web 7, is mounted, so as to be spaced apart from the base plate 2, on the combustion chamber structure 22 and in particular on the base plate 2. Whilst an additional, central web 7, which projects on the rear side, of the wall element 5 forms an edge 7.1 which delimits the wall element 5 in the direction of a through bore 18 for the fuel nozzle 77, the edge-side encircling web 7 forms radially outer and radially inner edges 7.2 in the direction of the cooling-air holes 3 for generating a cooling film 9 which cools the combustion chamber wall 4 and two lateral edges 7.3 which each extend radially and which each face toward similar wall elements 5 situated adjacent in a circumferential direction.

(19) In the installed state of the combustion chamber assembly, the edges 7.1, 7.2 and 7.3 define the (flow) chamber 6 in which a pressure prevails between the pressure at the compressor outlet and in the combustion space 21. With the flow guide device 10, the blow-off openings 10.1, 10.2 and 10.3 of which are formed for example from individual grooves or bores in the web 7, scavenging-air jets 12.1 flow out of said chamber 6 in the direction of interstices 15 between cooling-air jets 14 from the cooling-air holes 3 in order to scavenge the region outside the cooling-air holes 3. On the outer and the inner edge 7.2 of the wall element 5, that is to say in the direction of the inner and the outer combustion chamber wall 4, some of the blow-off openings 10.1, 10.2 and 10.3 of the flow guide device 10 in the central region of the edge 7.2 are arranged radially. In the vicinity of the corners of the wall element 5, blow-off openings 10.1 are inclined in the direction of the corner, in order to also scavenge the interstices 15 between the cooling-air jets 14 which are arranged between two adjacent wall elements 5.

(20) The blow-off openings 10.1, 10.2 and 10.3 of the flow guide device 10 may locally have a different orientation with respect to the extent direction of the edge-side web 7. Thus, in the simplest case, in particular if the radially extending edge 7.2 of the wall element 5 runs as an arc substantially parallel to a pitch circle 16 along which the cooling-air holes 3 are arranged, the blow-off openings 10.1 are formed as substantially radial grooves or bores which extend perpendicularly through the edge 7.2. The blow-off openings 10.1 (of a first type) are in this case arranged spaced apart from one another in a circumferential direction of the edge 7.2 and thus in a circumferential direction of the pitch circle 16 of the cooling-air holes 3, wherein a spacing of the blow-off openings 10.1 substantially corresponds to the spacing of the cooling-air holes 3 for forming a wall film 9 in a circumferential direction.

(21) In the region of the lateral edge 7.3 of the wall element 5, adjacent to a similar wall element which is situated adjacent in a circumferential direction, individual blow-off openings 10.2 (of a second type) of the flow guide device 10 are oriented substantially in the circumferential direction and are arranged such that the scavenging-air jets generated by adjacent wall elements 5 do not intersect. The flow passages, defined by the blow-off openings 10.2, of adjacent wall elements 5 which face one another are situated in planes which are mutually offset in an axial direction in order to prevent scavenging-air jets which are generated by means of said flow passages from intersecting.

(22) In the region of the corners of the wall element 5, provision is furthermore made for the orientation of the individual blow-off openings 10.3 (of a third type) in the web 7 to be adapted and for an angle to be provided which differs from 90° with respect to the extent of the web 7, such that the blow-off openings 10.3 point into those interstices 15 between the cooling-air holes 3 which are situated outside the region in which the edge 7.2 lies parallel to the pitch circle 16 of the cooling-air holes 3. Provision is made here whereby the scavenging-air jets of the scavenging-air flow 12 from the flow guide device 10 of the wall element 5 flow with a much lower speed into the interstices 15 between the cooling-air jets 14 from the cooling-air holes 3 in the base plate 2 than the cooling-air jets 14 themselves. This is achieved by means of the abovementioned much smaller pressure difference across the flow guide device 10 in relation to the cooling-air holes 3.

(23) FIG. 3 shows a schematic developed view along the flow path of the cooling-air jets 14 from the base plate 2 of the combustion chamber BK, which further downstream form the cooling film 9. Also illustrated here is the widening of the cooling film 9 in relation to the scavenging-air jets of the scavenging-air flow 12 from the wall element 5, which fill the interstices 15 that initially still exist between the cooling-air jets 14 over the component webs 20 between the cooling-air openings 3 in the base plate 2. Here, the individual cooling-air jets 14 are, in a first portion A1, still spaced apart from one another via edges 19 before, further downstream, they merge in a subsequent portion to form a closed cooling film 9 with cooling action. An interstice 15 between two adjacent cooling-air jets 14 can be filled by one or two scavenging-air jets 12. If two scavenging-air jets 12 flow through the same interstice 15, then they are generated with different spacings to the combustion chamber structure 22, for example the base plate 2, such that they do not disrupt one another. This figure illustrates a flow of the scavenging-air jets of the scavenging-air flow 12 through the interstice 15 in the same direction, as can also be seen from the arrangement according to FIGS. 4 and 5. A throughflow in opposite directions is alternatively possible, as can be seen from the arrangement in FIGS. 6A and 6B.

(24) FIG. 4 shows, with a view directed onto the rear side, multiple wall elements 5 with flow guide devices 10 for scavenging air, which are oriented such that the scavenging-air jets, generated by said flow guide devices 10, of the respective scavenging-air flows 12 flow through the interstices 15 between the cooling-air jets 14 from the combustion chamber structure 22 and scavenge the region outside the cooling-air holes 3 or outside the cooling-air jets 14. On the outer and the inner edge 7.2 of the wall element 5, that is to say in the direction of the inner and the outer combustion chamber wall 4, the flow guide devices 10 in the central region of the edge 7.2 are arranged radially. In the vicinity of the corners of the wall element, the axes 11 of the flow guide devices 10 are however inclined in the direction of the corner, in order to also scavenge the interstices 15 between the cooling-air jets 14 which are arranged between two wall elements 5.

(25) FIG. 5 shows a possibility of how, from adjacent wall elements 5.1 and 5.2, two scavenging-air jets can be generated from blow-off openings 10.1 and 10.2, which form flow passages, with different spacings to the combustion chamber structure 22. Here, both scavenging-air jets are directed toward the same interstice 15 between the cooling-air jets 14. In one wall element 5.1, a blow-off opening 10.1 of the flow guide device 10 is formed as a groove in the bearing surface of the edge 7.1 of the wall element 5.1 on the combustion chamber structure 22 (left). In the adjacent wall element 5.2, a blow-off opening 10.2 of the flow guide device 10 is formed as a bore through the edge 7.2 of the wall element 5.2. The section plane for the illustration in FIG. 5 has intentionally been laid through the interstice between the individual cooling-air holes 3 in the combustion chamber structure 22, such that the flow guide device 10 in the web 7 of the respective wall element 5.1 or 5.2 for generating a scavenging-air flow 12 lies clearly visible in the section plane of the illustration. The cooling-air holes 3 in the combustion chamber structure 22 of the combustion chamber BK for generating the cooling film 9 are however thus indicated merely as a dashed contour on the downstream wall element 5.2 in FIG. 5, because said cooling-air holes lie in a plane parallel to the section plane.

(26) FIG. 6A shows a longitudinal section through the combustion chamber BK with different wall elements 5.1, 5.2 and 5.3. One wall element 5.1 forms a heat shield, which is arranged on the base plate 2 of the combustion chamber structure 22. Wall elements 5.2 and 5.3 are situated further downstream and are fixed as combustion chamber shingles to the combustion chamber wall 4 that encloses the combustion space 21. FIG. 6B shows an enlarged detail from FIG. 6A, illustrating details of a gap 25 that is formed between two wall elements 5.2 and 5.3.

(27) The cooling-air openings 3 for forming the cooling film 9 with cooling action on the downstream wall elements 5.2 and 5.3 are situated both between wall elements 5.1, which are formed as a heat shield and situated adjacent to one another in a circumferential direction, on the base plate 2 and between the wall elements 5.2 and 5.3 on the combustion chamber wall 4. Analogously to the description above, corresponding flow guide devices 10 for generating scavenging-air jets of a scavenging-air flow 12 between cooling-air jets 14 may also be provided on wall elements 5.2 and 5.3 on the combustion chamber wall, in order that interstices 15 between the cooling-air jets 14 are adequately scavenged of combustion products. An angle α in the range from 70 to 120 degrees is enclosed between a wall element 5.1, which forms a heat shield mounted on the base plate 2, and a wall element 5.2 which adjoins the former wall element downstream and which forms a combustion chamber shingle. By contrast, an angle β of 150 to 210 degrees is enclosed, for example on the side facing toward the combustion space 21, between two wall elements 5.2 and 5.3 which follow one another in an axial direction and which each form a combustion chamber shingle.

(28) The scavenging-air jets of the scavenging-air flow 12 from the wall elements 5.2 and 5.3 which form combustion chamber shingles are generated by blow-off openings 10.1 and 10.2 of the flow guide devices 10 with different spacings in order that said scavenging-air jets do not impede one another as they flow through an interstice 15 between two cooling-air jets 14 in the gap 25 between the wall elements 5.2 and 5.3.

(29) Furthermore, an arrangement is also possible in which, in a circumferential direction, only every second interstice 15 between two cooling-air jets 14 is scavenged by a scavenging-air jet from the wall element 5.2, and the interstices 15 situated in between are scavenged from the wall element 5.3 in the opposite direction. Analogously, such an arrangement may also be used between wall elements 5.1 on the base plate 2 and wall elements 5.2 on the combustion chamber wall 4 in that, in a circumferential direction, only every second interstice 15 between two cooling-air jets 14 is scavenged by a scavenging-air jet from the wall element 5.1, and the interstices 15 situated in between are scavenged from the wall element 5.2 in the opposite direction.

(30) In the case of a combustion chamber assembly proposed in the synopsis of FIGS. 1 to 6B, each wall element 5, 5.1, 5.2, 5.3 has a flow guide device 10 for generating scavenging-air flows 12. The scavenging-air flows 12 are each directed toward the interstice 15 between in each case two cooling-air jets 14 of a row, arranged in a circumferential direction, of cooling-air holes 14 which are provided in a combustion chamber component 2 or 4 of the combustion chamber structure 22. On that part of the web 7 of a wall element 5, 5.1, 5.2, 5.3 which extends in the circumferential direction, said flow guide devices 10 are arranged purely radially or axially in the central region of an edge 7.2. In the vicinity of the corners of the wall element 5, 5.1, 5.2, 5.3, blow-off openings 10.2 as part of the flow guide devices 10 are however inclined in the direction of the corner, in order to also scavenge the interstices 15 between the cooling-air jets 14 which are arranged between two adjacent wall elements 5, 5.1, 5.2, 5.3.

LIST OF REFERENCE DESIGNATIONS

(31) 1 Cover of the base plate 2 Base plate 3 Cooling-air opening for forming the cooling film 4 Combustion chamber wall 5 Wall element 5.n n-th wall element 6 Chamber (between wall element 5 and combustion chamber 6.m structure) 7 Chamber between m-th wall element 5.m and combustion chamber structure 22 7.1 Web 7.2 Edge at burner bore 7.3 Edge at cooling film 8 Edge in circumferential direction Lip 9 Cooling film 10 Flow guide device for scavenging air (entirety) 10.n n-th flow guide device, individual/blow-off opening (passage or bore) 11 Axis of the guide device 12 Scavenging-air flow (formed from scavenging-air jets) 12.n Individual scavenging-air jet 13 Jet edge 14 Cooling-air jet for forming the cooling film 15 Intermediate space/interstice between two cooling-air jets 16 Pitch circle 17 Stud bolt for the fastening of the wall element 18 Through bore for burner 19 Edge of the cooling-air jet 20 (Component) web in base plate between cooling-air openings 21 Combustion space 22 Combustion chamber structure (with cover 1, base plate 2 and combustion chamber wall 4) 23 Impingement-cooling hole 24 Film-cooling hole 25 Gap 58 Arm 59 Flange 72 Outer casing 77 Fuel nozzle 111 Low-pressure compressor 112 High-pressure compressor 113 High-pressure turbine 114 Medium-pressure turbine 115 Low-pressure turbine E Inlet/Intake F Fan F1, F2 Fluid flow FC Fan casing L Longitudinal axis M Central axis/axis of rotation S Rotor shaft T (Turbofan) engine TT Turbine V Compressor α, β Angles