Combustion chamber shingle of a gas turbine and method for their preparation

The invention relates to a combustion chamber tile of a gas turbine and a method for their preparation.

Specifically, the invention relates to a combustion chamber tile with a plate-shaped base body which is provided with at least one Effusionskühlloch, soft extending through the body from a surface of one side to the other side, said Effusionskühlloch from one side of the base body from an inlet opening starting is formed over a part of its length substantially perpendicular to the surface.

Combustor shingles are characterized by the fact that they (often very high, several thousand) have any number of Effusionskühllöchern on the side directed toward the combustion chamber side. These effusion holes serve to cool the shingle against the high temperatures in the combustion chamber. In addition, located on the combustion chamber tile, at least one mixed air hole, which serves air from the space outside surrounding the combustion chamber (annular passage / annulus) into the combustion chamber for the purpose of cooling and Abmagerns the combustion and thus the reduction of the NOx formation in the combustion chamber to to guide. In addition to cooling by the Effusionskühllöcher, the shingles are provided with a ceramic coating acting as insulation against the high temperatures in the combustion chamber. The ceramic coating is thereby sprayed onto the combustion chamber-facing side of the shingle. The Effusionskühllöcher are frequently performed normal to the surface of the combustion chamber tile.

When coating the combustion chamber tile with a ceramic coating results in two primary ways. One possibility is to coat the shingle before the Effusionskühllöcher are introduced into the shingle. This means that the Effusionskühllöcher be drilled after the coating in the base body of the shingle. However, this leads to the spalling of the ceramic coating. In addition, it is necessary to form the Effusionskühllöcher by means of a drilling operation. This is very time-consuming and costly. An alternative is the shingle at first provided with the Effusionskühllöchern and coat afterwards. In this procedure, however, the problem arises that the Effusionskühllöcher be at least partially closed clogged by the coating composition and / or. From the prior art it is known for this purpose, for example, the cover Effusionskühlloch advance of coating (<patcit id="pcit0001" dnum="US4743462A"><text>US 4743462 A</text></patcit>) Or the mouth of the Effusionskühllochs be designed such that as little coating material can enter. Such solutions are known from<patcit id="pcit0002" dnum="US20090142548A1"><text>US 2009/0142548 A1</text></patcit> or the <patcit id="pcit0003" dnum="US20120094029A1"><text>US 2012/0094029 A1</text></patcit> previously known. A similar solution is also the<patcit id="pcit0004" dnum="EP0985802A1"><text>EP 0985802 A1</text></patcit>,

The invention has for its object to provide a combustion chamber tile of the aforementioned type and a method for their preparation, which allow the application of a subsequent coating with a simple structure and simple, cost-effective manufacturability without the risk of clogging of Effusionskühllöcher.

According to the invention the object is achieved by the combination of features of the independent claims, further advantageous embodiments of the invention result from the dependent claim.

The invention therefore provides that the Effusionskühlloch initially has a straight course within the main body of the combustion chamber tile and is subsequently provided with a bent course. The Effusionskühlloch does not extend, as in the prior art, a straight line through the combustion chamber tile. The prior art shows straight Effusionskühllöcher which is perpendicular (normal) extend this to the surface of the combustion chamber tile or at an angle. However, these previously known Effusionskühllöcher are always straight. In contrast, the embodiment of the invention has a distinct dog-leg which is formed in one, based on the total length of the Effusionskühllochs, the central region of Effusionskühllochs. It is particularly favorable when the Effusionskühlloch opposite the inlet opening of Effusionskühllochs forms a shoulder in the bearing the kinked course area. This shoulder forms a support surface on which can accumulate through the inlet opening which has entered the coating material. The coating material thus passes through the first rectilinear portion of the Effusionskühllochs and then is incident on the bent portion forming the shoulder mentioned. There, the coating material is deposited, without the risk that the Effusionskühlloch clogged. The bent portion or the shoulder thus formed are such that the size of the inlet opening corresponding volume of material can be deposited on the coating material there without that the cross section of Effusionskühllochs is narrowed or closed.

According to the invention a method of manufacturing a combustion chamber tile is also provided, which is produced by means of an additive Laseraufschmelzverfahrens, wherein in the production of at least one Effusionskühlloch is formed within a main body of the combustion chamber tile, which from a surface of the combustion chamber tile from an inlet opening, first of all a rectilinear course and being subsequently provided with a bent profile which opposite to the inlet opening forms a shoulder which extends substantially parallel to the surface and that, subsequently, the surface is provided with a surface coating as a spray coating, wherein the entering into the inlet opening material of the surface coating is deposited on the shoulder.

In a favorable embodiment of the invention provides that the shoulder extends parallel to the surface of the base substantially. Thus, there is a storage surface which is arranged opposite the inlet opening of Effusionskühllochs. In an alternative embodiment of the invention, it is also possible to form the shoulder to form a concave portion to the surface of the main body is inclined. The concave portion thus forms a collection volume, in which the coating material may accumulate. occurs also due to the viscosity of the coating material and its surface tension thus in this area of ​​the shoulder or the bent course of Effusionskühllochs a collection volume, in which the coating material can be safely deposited.

According to the invention thus have the Effusionskühllöcher a kinked course and have in the crease a depression or a widening of its diameter. This inevitably results through the bent course of Effusionskühllochs. The sprayed into the inlet opening of Effusionskühllochs volume amount of coating material thus deposited in the region of the bend or the shoulder without the Effusionskühlloch clogged. The further course of Effusionskühllochs to the uncoated side of the combustion chamber tile can be designed arbitrarily. The course of the Effusionskühllochs of the surface to be coated of the combustion chamber tile is preferably formed perpendicular to the surface.

The combustion chamber tile of the invention is preferably produced by a laser deposition method in which a powdery material is melted layer by layer using a laser. This makes it possible to generate arbitrary waveforms of Effusionskühllöchern.

In the following the invention will be described with reference to embodiments in conjunction with the drawing. In which:<dl id="dl0001"><dt>Fig. 1</dt><dd>a schematic illustration of a gas turbine engine according to the present invention;</dd><dt>FIG. 2</dt><dd>a schematic side sectional view of an inventively to use combustion chamber;</dd><dt>Fig. 3</dt><dd>a plan view and a side view of the combustion chamber tile of the prior art;</dd><dt>Fig. 4</dt><dd>a side view, analogous <figref idrefs="f0003">Fig. 3</figref>, With an applied coating;</dd><dt>Fig. 5</dt><dd>a sectional view analogous to <figref idrefs="f0004">Fig. 4</figref>, With inventively embodied Effusionskühllöchern; and</dd><dt>Fig. 6</dt><dd>further embodiments of the invention.</dd></dl>

The gas turbine engine 10 according to <figref idrefs="f0001">Fig. 1</figref> is a well-presented example a turbomachine, in which the invention may find application. The engine 10 is formed in a conventional manner and comprises in flow series an air intake 11, a revolving in a housing fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustor 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and a exhaust nozzle 19, all disposed about a central engine axis 1st

The intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which has a groove extending in the circumferential direction arrangement fixed stationary vanes 20, which are generally referred to as a stator and the radially inwardly from the engine case 21 in an annular flow channel through the compressors 13, 14 protrude. The compressors have further to an arrangement of compressor rotor blades 22, which protrude radially outwardly from a rotatable drum or wheel 26 that are coupled to hub 27 of the high pressure turbine 16 and the medium-pressure turbine 17th

The turbine sections 16, 17, 18 have similar stages, comprising an array of fixed guide vanes 23, which protrude radially inwards from the housing 21 in the annular flow channel through the turbines 16, 17, 18, and a subsequent array of turbine blades 24, the protruding outwardly from a rotatable hub 27th The compressor drum or compressor disk 26 and the blades 22 disposed thereon and the Turbinenrotornabe 27 and disposed thereon turbine blades 24 rotate during operation around the engine axis. 1

The <figref idrefs="f0002">FIG. 2</figref> schematically shows the structure of a present invention to be used, known from the prior art combustion chamber 15. This fuel nozzle 29 includes a combustion chamber and an outer casing 30 and a combustor inner casing 31. The reference numeral 32 is shown a combustion chamber wall. At the outlet of the combustion chamber is a Turbinenvorleitreihe 33. At the combustion chamber wall 32 are 34, which may have Zumischlöcher 35 combustor shingles. The air flows in the inflow direction 36 through the combustion chamber. Cooling air is Effusionskühllöcher 37 (s.<figref idrefs="f0003">Fig. 3</figref>) Passed through the combustion chamber tile 34th To fix the combustion chamber tile 34 screws 38 can be used with nuts. 39 As is clear from the<figref idrefs="f0004">Fig. 4</figref> shows the combustion chamber tile 34 has a ceramic coating (coating surface) 40 which is sprayed onto the combustion chamber tile 34 (coating direction 43 according <figref idrefs="f0004">Fig. 4</figref>).

The <figref idrefs="f0002">FIG. 2</figref> shows the structure of the combustion chamber further comprises a combustion chamber head 41 and a heat shield 42nd

The <figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> each show a schematic sectional view of the structure of the combustion chamber tile inventive analog <figref idrefs="f0004">Fig. 4</figref>, In the<figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> each represented different gradients and cross-sectional shapes of Effusionskühllöcher invention 37, the arrangement and presentation of Effusionskühllöcher made only for the purpose of illustrating the invention and must be not necessarily in this distance of Effusionskühllöcher and this partly formed assembly.

It follows that the surface 44 of the combustion chamber tile 34 is sprayed in the direction of coating 43 with a ceramic coating 40th Here, the coating 40 is deposited on the areas of the combustion chamber tile 34, on which no Effusionskühllöcher are 37th In the area of ​​inlet openings 45 of Effusionskühllöcher the material of the ceramic coating 40 in the first straight line and vertically enters the surface 44 extending region 46 of Effusionskühllöcher 37th The Effusionskühlloch then instructs the straight course 46 on a bend or kinked History 47th In these bent curve 47 results in a cross-sectional widening of the Effusionskühllochs 37. Further, it is formed a shoulder 48 which provides a support surface that is disposed substantially opposite to the inlet opening 45, so as shown by the three left-hand embodiments in accordance with<figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> explain. The entering through the inlet opening 45 coating material 40 is thus accumulated on the shoulder 48 and remains there, so as shown in<figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> is shown.

It is understood that the designated port 45 as an entry opening of the combustion chamber tile is defined in terms of the application of the ceramic coating 40 as the inlet opening. The course of the cooling air is such that it exits at the coating inlet opening 45, because the ceramic coating 40 is on the inside relative to the combustion chamber 15, respectively.

The shoulder 48 and the bent course of 47 can also be formed so that forms a pocket or a concave portion, so as in particular to the embodiments of the three right <figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> is shown. This leads to an even more secure deposition of the coating material 40th

The remaining history Effusionskühllöcher invention may be any, he may have rounded or angular shapes. The exit of the Effusionskühllochs to the non-coated side of the combustion chamber tile 34 can be formed perpendicular to this surface, or at an angle.

As above described, the ceramic coating 40 is at the interior of the combustion chamber 15 facing side of the combustion chamber tile 34, so that the flow direction in accordance with cooling air <figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> from bottom to top. The cooling air thus emerges through the inlet opening 45 and thus runs counter to that in the<figref idrefs="f0004">Fig. 5</figref> and <figref idrefs="f0005">6</figref> Coating direction 43 shown with which the ceramic coating 40 is sprayed on.

LIST OF REFERENCE NUMBERS

<dl id="dl0002" compact="compact"><dt>1</dt><dd>Engine axis</dd><dt>10</dt><dd>Gas turbine engine / core engine</dd><dt>11</dt><dd>air inlet</dd><dt>12</dt><dd>fan</dd><dt>13</dt><dd>Medium pressure compressor (compressor)</dd><dt>14</dt><dd>High pressure compressor</dd><dt>15</dt><dd>combustors</dd><dt>16</dt><dd>High pressure turbine</dd><dt>17</dt><dd>Intermediate-pressure turbine</dd><dt>18</dt><dd>Low pressure turbine</dd><dt>19</dt><dd>exhaust nozzle</dd><dt>20</dt><dd>vanes</dd><dt>21</dt><dd>Engine casing</dd><dt>22</dt><dd>Compressor blades</dd><dt>23</dt><dd>vanes</dd><dt>24</dt><dd>turbine blades</dd><dt>26</dt><dd>Compressor drum or disc</dd><dt>27</dt><dd>Turbinenrotornabe</dd><dt>28</dt><dd>outlet cone</dd><dt>29</dt><dd>fuel nozzle</dd><dt>30</dt><dd>Combustor outer casing</dd><dt>31</dt><dd>Combustor inner casing</dd><dt>32</dt><dd>combustion chamber wall</dd><dt>33</dt><dd>Turbinenvorleitreihe</dd><dt>34</dt><dd>combustion chamber tile</dd><dt>35</dt><dd>Zumischloch</dd><dt>36</dt><dd>inflow</dd><dt>37</dt><dd>Effusionskühlloch</dd><dt>38</dt><dd>(Thread) -Stift</dd><dt>39</dt><dd>mother</dd><dt>40</dt><dd>ceramic coating (surface coating)</dd><dt>41</dt><dd>bulkhead </dd><dt>42</dt><dd>heat shield</dd><dt>43</dt><dd>coating direction</dd><dt>44</dt><dd>surface</dd><dt>45</dt><dd>inlet opening</dd><dt>46</dt><dd>straight course</dd><dt>47</dt><dd>Knick / kinked History</dd><dt>48</dt><dd>shoulder</dd></dl>