EP3182011B1 - Wall of a component to be cooled using air cooling, in particular of a gas turbine combustion chamber wall - Google Patents

Description

The invention relates to a wall of a cooling air to be cooled component according to the preamble of claim 1 and a method for producing a wall, in particular a gas turbine combustor wall.

In detail, the invention relates to a wall of a component, which is provided for cooling by means of cooling air with at least one cooling air duct. The cooling air channel is arranged at least in its outflow region inclined at an angle to the wall. The wall is acted upon by cooling air from one side, through the cooling air duct, the cooling air flows to the other side of the wall. In this case, the cooling air cools the wall as it flows through the cooling air channel and then lays as a cooling air film on the thermally loaded side of the wall to shield it.

In particular, the invention relates to a gas turbine combustor wall, and more particularly to an inner combustor wall provided with effusion holes for passing cooling air and cooling the hot side surface of the inner combustor wall.

From the prior art it is known, when cooling wall elements or walls, to arrange the cooling air ducts at an angle in order to increase the effective running length of the cooling air duct. This embodiment, however, limits, since the angular arrangement of the cooling air ducts is possible only up to an angle at which still takes place a sufficient flow. As an example, this is on the US 5,000,005 A directed. This document shows a gas turbine combustor with effusion holes, which are widened in the discharge and form a diffuser. Usual inclination angle of cooling air ducts lie in an angular range between 15 ° and 45 °, measured between the central axis of the cooling air duct and the surface of the wall.

In order to extend the overall length of the cooling air channel, it has been proposed to increase the overall wall thickness. However, this leads to a significant increase in weight and therefore proves to be disadvantageous. This is on the WO 95/25932 A1 directed.

From the US 2011/005233 A1 For example, a wall is known which is provided with ribs for lengthening the overall length of the cooling air ducts.

Furthermore, the shows EP 2 942 487 A1 a profile, for example a blade profile for rotors or stators of a gas turbine engine. The profile has cooling holes formed along axes, the axes being oblique with respect to an outer profile surface. Projections are provided on an inner side of the profile through which the cooling holes extend and which can either be oriented obliquely or parallel with respect to the respective axis. The cooling holes can be introduced by various processes, such as laser or water jet cutting. Alternatively, the entire component can be manufactured by means of an additive process.

The invention has for its object to provide a means of cooling air to be cooled wall of a component, which ensures optimized cooling with a simple structure and simple, cost manufacturability.

According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.

According to the invention it is thus provided that the cooling air channel is formed tubular extended on the side of the supply of cooling air. The cooling air duct thus extends through the wall to be cooled and protrudes in the form of a tubular extension over the surface at which the cooling air is supplied. On the one hand, this leads to the fact that the entire length of the cooling air duct increases. The tubular extension thus forms an additional cooling surface for the cooling air flowing through the cooling air channel, so that the wall can be cooled better overall.

Furthermore, the tubular extension according to the invention causes an enlarged outer surface is created, namely the tubular approach, which is also used for heat transfer, since it is flowed around by the cooling air.

To fulfill this task of heat transfer even better, the tubular extension is connected to the wall exposed to the hot gas by a rib, so that the heat through the rib from the wall into the tubular Extension can be directed. This increases the temperature of the tubular extension and thereby improves the cooling effect of the overall system. The tubular extension is further disposed at an angle to the surface of the wall. The rib supports the tubular extension opposite the surface of the wall. The angle at which the tubular extension is arranged to the surface of the wall, according to the invention is an acute angle, in particular in an angular range between 15 ° and 45 °. More preferably, a maximum width of the tubular extension of the cooling air channel is greater than a maximum width of the rib. The width of the rib is preferably constant. Alternatively, the rib at the foot region, on which the rib is arranged on the wall, a greater width than at a connection region to the tubular extension of the cooling air duct.

An additional effect that improves cooling is that the tubular projection projecting over the surface of the side of the wall results in turbulence of the cooling air. This also increases the heat transfer coefficient.

Overall, the tubular projections or extensions can have a relatively small volume, so that the overall weight of the wall as a whole becomes only insignificantly larger. This proves to be particularly advantageous for components whose weight is to be minimized.

A particularly advantageous application of the solution according to the invention consists in inner, hot combustion chamber walls of combustion chambers of gas turbines. But other, to be cooled by cooling air wall elements can be further developed according to the invention, for example, walls of turbine blades, which are cooled by cooling air ducts in the interior of the turbine blades.

In an advantageous embodiment of the invention it is provided that a part of the flow length of the cooling air channel is formed as a diffuser, which extends substantially through the entire thickness of the wall. In the solutions known from the prior art only a small length of the cooling air duct can be used as a diffuser, since the wall thickness limits the diffuser length. By means of the tubular projections, a possibility according to the invention is created for substantially increasing the effective length of the diffuser, wherein the diffuser can not only be formed over the entire thickness of the wall, but additionally also over a partial region of the tubular extension.

The inventively provided tubular approach of the wall can be made in different ways. When the wall is made as a casting, the entire cooling air channel, also the region in which it extends through the tubular extension or the tubular extension, has a rectilinear course with a straight axis. The tubular extension can be slightly conical in this case in order to have a draft angle suitable for the casting process. The cooling air duct can be generated by means of laser or by spark erosion. The rib between the wall and the tubular extension increases the stability of the wax model for casting in the lost mold and also improves the filling of the tubular extension during the actual casting process.

Even with a generative production of the wall according to the invention or of the walled component (laser deposition welding method or the like), the support of the tubular extension by means of a rib is helpful. The rib ensures a production-optimized design of the geometry, since there are no free-standing parts and therefore no support structures must be provided, the be removed later. According to the invention, during the generative production, first a part of the rib is produced and thereafter the tubular extension together with the rest of the rib. In such a wall, it is also possible to bend the cooling air duct, for example, arcuate. This means that the cooling air duct on the side of the cooling air supply to the surrounding surface has a greater angle, as in the exit region on the thermally loaded side of the wall. In this case, the orientation of the rib results from the direction of the generative structure, that is, substantially perpendicular to the base plate on which the individual layers are produced during the generative production, and deviates from this direction according to the invention not more than ± 30 °. However, the direction of the curvature of the cooling air channel results from the requirements of component cooling. Near the combustion chamber head or in front of or behind wall openings such as mixing holes or access holes for spark plugs, it may be useful that the outlet of the cooling air duct has a different angle to the axis of the engine than the inlet, for example 30 ° at the inlet and 45 ° at the outlet, to guide the cooling air duct around such wall openings. Overall, it may thus be advantageous that the rib and the cooling air channel have two different orientations.

According to the invention, the center axis of the cooling air channel and the rib central axis of the rib are provided such that the two center axes are arranged at an acute angle to one another. The angle is preferably between 15 ° and 45 ° and is particularly preferably 30 °.

More preferably, the wall comprises an obstacle, in particular an opening, such as a mixed air opening or an access hole for a spark plug, wherein along the circumference of the obstacle, a plurality of cooling air ducts are arranged with ribs. In particular, when the center axes of the cooling air duct and the rib intersect, a cooling flow around the obstacle on the thermally loaded side of the wall can be achieved by the arrangement of a plurality of cooling air ducts.

More preferably, the central axis of the cooling air channel is directed parallel to a flow which is present on the thermally loaded side of the wall. This results in improved cooling of the thermally loaded wall.

According to the invention, the inlet region of the tubular extension of the cooling air channel can furthermore be designed to be flow-optimized. It can be either sharp-edged, beveled or rounded.

According to the invention, the cross-section of the cooling air duct when used in an inner combustion chamber wall may have any shapes, for example circular, elliptical or in the form of a slot. In the latter case, the cooling air duct can be dimensioned, for example, 0.5 mm x 1.8 mm in size.

As already mentioned, the tubular extension of the cooling air duct in connection with the rib leads to an additional turbulence of the inflowing cooling air and thus results in an improved heat transfer.

When using the inventively designed wall in a double-walled gas turbine combustor, the length of the tubular extension or the tubular extension of the cooling air duct is dimensioned such that it serves as a spacer to the outer combustion chamber wall. Accordingly, the orientation of the surface formed by the inlet region perpendicular to the central axis of the cooling air passage is selected so as not to be perpendicular to the surface of the cooling air supply side of the wall. This would lead to a closure of the inlet region upon contact with an outer combustion chamber wall. It is thus an angular arrangement is provided, which extends for example only up to about 45 °. This allows a sufficiently large inflow even when in contact with the outer combustion chamber wall. The orientation of the surface through which the cooling air flows into the cooling air duct is determined by the particular manufacturing method used. This also results in that the cooling air channel is not arranged perpendicular to the surface of the side of the cooling air supply of the wall. In the case of a casting, the orientation is determined by the Entformungsschräge. In the case of generative generation, the orientation of the surface is determined by the ability of the respective generative method to produce overhanging structures without additional support structure, since an additional support structure would later have to be laboriously removed again.

When the wall according to the invention is used as the inner combustion chamber wall of a double-walled gas turbine combustor, it may happen that an obstruction, such as a mixing air hole or front shingle edge, for example towards a combustion head, is positioned in the inflow region of the tubular extension of the cooling air passage. In this case, it is possible according to the invention, as already indicated above, form the tubular extension arcuate or more curved. In this case, the overall height of the tubular extension would be less than the distance between the inner and outer combustion chamber walls. It would thus result in a distance corresponding to 0.5 to 2 x the hydraulic diameter of the cooling air duct. Thus, it is avoided that the inlet region of the tubular extension is blocked in a thermal distortion, because the inner combustion chamber wall would get in contact with the outer combustion chamber wall at the edge of the mixing air hole or at the shingle edge. In any case, the inlet region for the cooling air remains open in the cooling air duct.

With regard to the possibility of forming a diffuser in the wall, the invention thus provides the possibility of starting the diffuser at a greater distance from the thermally loaded side of the wall. At the same opening angle of the diffuser thus results in comparison to the prior art, a significant extension of the diffuser, without an increase in the cooling air flow rate is required.

As is apparent from the above description, the invention is characterized by a number of significant advantages:
Due to the tubular extension of the cooling air channel, the inner surface of the cooling air channel is increased, so that there is an increased heat transfer.

In addition, by the tubular extension and the surface of the side of the wall on which the cooling air supply is increased. This surface is usually cooled by an impact cooling when using the wall according to the invention in a gas turbine combustor. By enlarging the surface, more heat is absorbed by the cooling air, so that the overall temperature of the wall can be lowered.

The tubular extension results in an increase in the degree of turbulence of the flow in the impingement cooling cavity, namely the gap between the outer and inner combustion chamber walls, in which cooling air is supplied through impingement cooling holes to the outer combustion chamber wall. This also leads to an increased heat transfer.

As a result of the possibility created according to the invention of increasing the effective length of the diffuser and of further opening it at its outlet opening at a constant opening angle, the flow velocity of the cooling air flowing through the cooling air duct is reduced. Due to the lower flow velocity of the cooling air, the film cooling effect is increased.

By the rib, by means of which the tubular extension is supported on the surface of the side of the cooling air supply to the wall, in addition heat is dissipated from the wall and passed into the tubular extension. There it can be discharged to the outside in the extended cooling air duct and also from the tubular extension to the outside to the surrounding air. The flow around the rib by cooling air results in additional cooling of the wall.

When using the wall of the invention in a double-walled gas turbine combustor, the tubular extension ensures the maintenance of a distance between the outer and inner combustion chamber walls. This ensures that even in the case of thermal distortions, in particular of the inner combustion chamber wall, the impingement cooling through the impingement cooling holes of the outer combustion chamber wall can take place unhindered, since closure of the impingement cooling holes is prevented. Thus, the cooling air can flow through the baffle cooling holes in the intermediate region between the outer and the inner combustion chamber wall unhindered.

The rib leads to the advantage that the wall according to the invention can be produced with a preferred geometry, be it as a casting or in a generative process by which heat is conducted from the thermally loaded wall into the tubular extension and can be absorbed by the air there ,

A flow optimization, for example, a significant rounding of the inlet region of the tubular extension ensures that the flow applies to the entire inner wall of the cooling air channel and creates a good heat transfer.

Furthermore, the invention relates to an additive method for producing a wall according to one of claims 1 to 9. According to the invention, the additive method is designed such that the cooling air duct and the rib are made additive, such that the rib provides support of the cooling air duct during the manufacturing process ,

Fig. 1

eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung,

Fig. 2

eine Längs-Schnittansicht einer Brennkammer gemäß dem Stand der Technik,

Fig. 3

eine perspektivische Teil-Ansicht zweier beispielhafter Ausgestaltungsvarianten einer Wand mit rohrförmig verlängerten Kühlluftkanälen,

Fig. 4

eine vereinfachte Schnittansicht, analog Fig. 3,

Fig. 5

eine perspektivische Ansicht einer weiteren beispielhaften Ausgestaltungsvariante,

Fig. 6

eine vereinfachte Schnittansicht, analog Fig. 5,

Fig. 7

eine weitere Schnittansicht einer Ausgestaltungsvariante zur Darstellung des Diffusors,

Fig. 8

eine Draufsicht einer erfindungsgemäßen Ausgestaltungsvariante einer Wand mit einem Hindernis,

Fig. 9

eine Draufsicht einer weiteren erfindungsgemäßen Ausgestaltungsvariante, und

Fig. 10a-10f

schematische Darstellungen eines additiven Verfahrens zur Herstellung einer beispielhaften Wand eines Bauteils.

In the following the invention will be described by means of embodiments in conjunction with the drawing. Showing:

Fig. 1

a schematic representation of a gas turbine engine according to the present invention,

Fig. 2

a longitudinal sectional view of a combustion chamber according to the prior art,

Fig. 3

2 is a partial perspective view of two exemplary embodiments of a wall with tubular extended cooling air ducts,

Fig. 4

a simplified sectional view, analog Fig. 3 .

Fig. 5

a perspective view of another exemplary embodiment variant,

Fig. 6

a simplified sectional view, analog Fig. 5 .

Fig. 7

a further sectional view of an embodiment variant for illustrating the diffuser,

Fig. 8

a top view of an embodiment variant according to the invention of a wall with an obstacle,

Fig. 9

a plan view of a further embodiment variant according to the invention, and

Fig. 10a-10f

schematic representations of an additive method for producing an exemplary wall of a component.

The gas turbine engine 110 according to Fig. 1 is a generalized example of a turbomachine, in which the invention can be applied. The engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119 with an outlet cone, which are all arranged around a central engine center axis 101.

The intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, that radially inwardly from the engine casing 121 in an annular flow passage through the compressors 113, 114 protrude. The compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disc 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.

The turbine sections 116, 117, 118 have similar stages, comprising an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124, projecting outwardly from a rotatable hub 126. The compressor drum or compressor disk 125 and the vanes 122 disposed thereon and the turbine rotor hub 126 and turbine blades 124 disposed thereon rotate about the engine centerline 101 during operation.

The Fig. 2 shows a longitudinal sectional view of a known from the prior art combustion chamber wall in an enlarged view. Here is a combustion chamber 1 with a Central axis 9 shown, which includes a combustion chamber head 3, a base plate 8 and a heat shield 2. A burner seal is provided with the reference numeral 4. The combustion chamber 1 has an outer cold combustion chamber wall 7, to which an inner, hot combustion chamber wall 6 is attached. For supplying mixed air mixing air holes 5 are provided. The presentation of impingement cooling holes and effusion holes has been omitted for clarity.

The inner combustion chamber wall 6 is provided with bolts 13, which are designed as threaded bolts and are screwed by means of nuts 14. The storage of the combustion chamber 1 takes place via combustion chamber flanges 12 and combustion chamber suspensions 11. Denoted by 10 is a sealing lip.

The Fig. 3 shows in perspective partial view embodiments of an exemplary wall 16. On the wall acting as effusion holes cooling air channels 15 are formed. These can, as in the right half of the Fig. 3 represented, have a circular cross section or, as shown in the left half of the figure, be provided with an elongated cross section. The reference numeral 22 shows an inlet region of the respective cooling air channel 15. From the illustrations of Fig. 3 shows that the cooling air channels 15 are formed tubular extended. The tubular extensions 19 are inclined at an angle 23 to the surface of a side 17 of the wall 16, which is supplied with cooling air. The tubular extensions 19 are each supported by a rib 21. The rib 21 serves on the one hand to simplify the production of the wall. On the other hand, the rib 21 forms an additional surface, in addition to the surface of the tubular extension 19, which is surrounded by cooling air and thus forms a heat transfer surface. Due to the rounded, streamlined inlet region 22, there is an improved inflow into the cooling air channels 15.

The Fig. 4 shows a simplified sectional view of the embodiment of Fig. 3 The result is that a central axis 24 of the rectilinear cooling air channel 15 formed in this embodiment is inclined at an angle 23 to the surface of the side 17 of the wall 16. This angle can be between 15 ° and 45 °. For simplicity, in Fig. 4 the angle 23 between the side 17 and the dashed outline shown outer contour of the tubular extension 19 located.

The Fig. 4 further shows parallel to the wall 16, an outer combustion chamber wall 7. This has to the wall 16, which forms an inner combustion chamber wall (s. Fig. 2 ) at a distance in which cooling air is introduced by not shown impingement cooling holes. The tubular extension 19 additionally forms a spacer between the wall 16 and the Combustion chamber wall 7. In a thermal distortion of the wall 16 is thus always ensured that a sufficient volume for the passage of cooling air is maintained.

The inlet region 22 of the tubular extension 19 forms a surface 25 which is inclined at an angle to the surface of the side 17 of the wall 16. Even if a contact between the combustion chamber wall 7 and the tubular extension 19 would occur, the inlet region 22 of the cooling air channel 15 would continue to be free, so that an inflow of cooling air into the cooling air channel is ensured.

The Fig. 4 shows by reference numeral 18 a thermally loaded side of the wall 16. This will be described below in connection with the Fig. 4 explained in detail.

The FIGS. 5 and 6 show a design variant of the tubular extension 19, in which the tubular extension 19 is arranged in its inlet region substantially parallel to the side 17 of the wall 16. This embodiment variant is preferably selected when the cooling air channel 15 is formed adjacent to an edge 26, for example a shingle edge or at the edge of a mixing air hole 5. A straight-line cooling air duct 15, as in Fig. 4 would not lead to optimal inflow of cooling air. Therefore, in the embodiment of the FIGS. 5 and 6 formed the entire cooling air duct 15 bent. It is understood that the height of the tubular extension 19 is less than the height of the edge 26, so that it is also in a direct contact of the wall 16 with the combustion chamber wall 7, not shown (s. Fig. 4 ) does not lead to a closure of the inlet region 22.

Also in the embodiment of FIGS. 5 and 6 is, as in the previous embodiment, the inlet region 22 rounded and designed to optimize flow.

The Fig. 7 shows a sectional view through the wall, for example according to the embodiment of Fig. 4 , The cutting direction is chosen so that a diffuser 20 is shown, which opens to the thermally loaded side 18 of the wall 16. From the sectional view of Fig. 7 it follows that the wall thickness ratios are not to scale for the purpose of clarity of illustration. The reference numeral 27 shows with the left arrow the effective cross section of the cooling air channel 15. After a predetermined running length of the cooling air channel 15 in the tubular extension 19 begins, as shown by solid lines, in the region of the reference numeral 28, the diffuser 20. From the illustration it can be seen that at a constant diffuser angle (relative to the central axis 24 of the cooling air channel 15) of the staggered beginning of the diffuser 20 leads to a larger opening and thus to a larger cross section 29 of the cooling air duct outlet.

In comparison, the shows Fig. 7 in dashed lines the situation of the prior art. Without the tubular extension 19, it would be necessary to maintain the cross-section 27 of a shortened cooling air passage over part of the thickness of the wall 16. The beginning of the diffuser would be set back in the direction of the thermally loaded side 18, resulting in a much smaller cross-section 29 in the region of the cooling air outlet of the cooling air duct 15.

Fig. 8 shows an embodiment variant of the invention, in which an obstacle 30, for example a mixed air opening, is provided in the wall 16. Along the circumference of the obstacle, a plurality of cooling air channels 15 are arranged on the side 17 of the cooling air supply. How out Fig. 8 it can be seen, a central axis 24 of the cooling air channels 15 is arranged at an acute angle 31 to a rib central axis 32. How out Fig. 8 it can be seen, the arrangement of the cooling air channels 15 along the circumference of the obstacle 30 allows sufficient cooling on the thermally loaded side along the circumference of the obstacle. The cooling air channels 15 are each formed with a tubular extension and a diffuser and in Fig. 8 shown only schematically.

Fig. 9 shows a further embodiment of the present invention, wherein a plurality of cooling air channels 15 is provided. The central axes 24 of the cooling air channels 15 are as in Fig. 8 shown embodiment arranged at an acute angle 31 to the rib central axis 32. How out Fig. 9 it can be seen, is an orientation of the cooling air channels 15 such that they are parallel to a flow 33 on the thermally loaded side, which in Fig. 9 indicated by the dashed arrow (flow 33). As a result, a particularly good cooling of the thermally loaded side 18 of the wall 16 is achieved.

The 10a to 10f show an example of a production of an exemplary wall of a component. In this embodiment, the component is a combustion chamber wall. The method is an additive method, wherein the arrow 34 shows a construction direction of the additive method. How out Fig. 10a it can be seen, the wall 16 is first built up additive. In Fig. 10b it is shown how the starting ribs 21 'are built up. The ribs 21 are in Fig. 10c built up to the beginning of the cooling air duct 15, wherein in Fig. 10c then already the beginning of the construction of the cooling air duct 15 begins. Fig. 10d shows that with further structure in construction direction 34, the cooling air channels slowly arise, the cooling air channels are supported on the rib 21. The further emergence of the cooling air ducts is off 10e and 10f seen. Thus, as from the 10a to 10f it can be seen, in the mounting direction 34, a vertical production of the component are made possible by means of an additive method. The structure of the rib 21 supports the cooling channel 15. In this example, the tubular extension 19 of the cooling air channel 15 runs straight on the rib 21. Like in Fig. 3 are in the 10a to 10f exemplified two variants with different cross sections of the cooling air ducts shown. When the central axis of the cooling air passages 15 and the rib center axis 32 intersect, as in FIGS Fig. 8 and 9 is shown, the construction direction 34 is parallel to the rib central axis 32. This is schematically in the Fig. 8 and 9 located.

LIST OF REFERENCE NUMBERS

1

combustion chamber

2

heat shield

3

bulkhead

4

Brenner seal

5

mixed air

6

inner, hot combustion chamber wall / segment / shingles

7

outer, cold combustion chamber wall

8th

baseplate

9

central axis

10

sealing lip

11

combustion chamber suspension

12

Brennkammerflansch

13

bolt

14

mother

15

Effusion / cooling air duct

16

wall

17

Side of the cooling air supply

18

thermally loaded side

19

tubular extension

20

diffuser

21

rib

22

intake area

23

corner

24

central axis

25

surface

26

edge

27

cross-section

28

Beginning diffuser

29

cross-section

30

Obstacle / mixed air opening / access hole

31

acute angle

32

Rip central axis

33

Flow at the thermally loaded side

34

Structure of the additive method

101

Engine centerline axis

110

Gas turbine engine / core engine

111

air intake

112

fan

113

Medium pressure compressor (compressor)

114

High pressure compressor

115

combustion chamber

116

High-pressure turbine

117

Intermediate pressure turbine

118

Low-pressure turbine

119

exhaust nozzle

120

vanes

121

Engine casing

122

Compressor blades

123

vanes

124

turbine blades

125

Compressor drum or disc

126

Turbinenrotornabe

127

outlet cone

Claims (11)

1. Wall for a component which is to be cooled by means of cooling air and which has at least one cooling-air duct (15), which cooling-air duct, at least in its outflow region, is arranged inclined at an angle to the wall (16) and passes through the wall (16) from one side (17), on which cooling air is fed, to a thermally loaded side (18), wherein the cooling-air duct (15) has a tubular extension (19) on the side (17) of the feeding of cooling air, wherein the tubular extension (19) is arranged at an acute angle (23) to the surface of the wall (16), characterized in that the tubular extension (19) is supported with respect to the surface of the wall (16) by means of a rib (21), wherein a central axis (24) of the cooling-air duct (15) is arranged at an acute angle (31) to a rib central axis (32) of the rib (21).
2. Wall according to Claim 1, characterized in that a part of the flow length of the cooling-air duct (15) is in the form of a diffusor (20) which extends substantially through the entire thickness of the wall (16).
3. Wall according to Claim 1 or 2, characterized in that the tubular extension (19) is of conical form at its outer contour.
4. Wall according to one of Claims 1 to 3, characterized in that the cooling-air duct (15) is of rectilinear or arcuate form.
5. Wall according to one of Claims 1 to 4, characterized in that an inflow region (22) of the tubular extension (19) of the cooling-air duct (15) is formed in a flow-optimized manner.
6. Wall according to one of Claims 1 to 5, characterized in that the wall (16) is in the form of a casting.
7. Wall according to one of Claims 1 to 6, characterized in that the wall (16) is in the form of an additively manufactured component.
8. Wall according to Claim 1, also comprising an obstacle (30) and in particular an opening, wherein a multiplicity of cooling-air ducts (15) having ribs (21) is arranged along the periphery of the obstacle (30).
9. Wall according to one of the preceding claims, wherein the central axis (24) of the cooling-air duct (15) is arranged parallel to a flow (33) on a thermally loaded side of the wall.
10. Gas turbine combustion chamber wall having an outer combustion chamber wall (7) on which an inner combustion chamber wall (6) is mounted with a spacing, said inner combustion chamber wall being provided with multiple effusion holes (15) which are arranged inclined to the inner combustion chamber wall (6), characterized in that the inner combustion chamber wall (6) is formed according to one of the preceding claims.
11. Additive method for producing a wall according to one of Claims 1 to 9, wherein the additive method is designed such that the cooling-air duct and the rib (21) are produced additively such that the rib (21) provides a support for the cooling-air duct (15) during the production process.

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