JP2015511696A - Improved hole arrangement in the liner of the combustion chamber of a gas turbine engine with low combustion dynamics and low emissions. - Google Patents

Abstract

A gas turbine combustion chamber having an inner housing and an outer housing. The inner housing has an inner wall element (501) having a first hole arrangement and a second hole arrangement. The inner wall element surrounds the combustor volume. The first hole arrangement has first holes arranged at a first surface density, the second hole arrangement has second holes arranged at a second surface density, and the first surface density. Is different from the second surface density. The outer housing has an outer wall element (502) having a further first hole arrangement and a further second hole arrangement. The outer wall element (502) of the outer housing surrounds the inner wall element (501) of the inner housing, thus forming a gap therebetween. The further first hole arrangement has a further first hole arranged at a further first surface density, and the further second hole arrangement has a further second hole arranged at a further second surface density. However, the further first surface density is different from the further second surface density.

Description

  The present invention relates to a housing for a combustion chamber for a gas turbine and to a method for manufacturing a combustion chamber for a gas turbine.

  In the field of gas turbine technology, the objective is to reduce the production of environmental pollutants such as nitrogen oxides (NOx), carbon monoxide (CO), unburned hydrocarbons (UHC). Accordingly, it is an object to achieve a reliable and stable lean combustion process in the combustion chamber of a gas turbine.

  In order to provide a lean burn combustion process, more air is directed toward the front end of the combustion chamber (initiating the combustion process) and mixed with fuel in the combustor. This is accomplished by rebalancing the effective area, i.e., the accumulated hole area of the combustion can and the accumulated hole area of the combustor or swirler. However, as more airflow is directed through the front end, the combustion chamber facilitates combustion instability, which is an inherent problem associated with lean burn combustion.

  In order to suppress combustion instability, particularly combustion dynamics inside the combustion chamber, the wall elements of the combustion chamber housing are provided with holes through which they exchange gas.

  Patent Document 1 discloses a gas turbine engine combustor, which includes an inner combustor wall and an outer combustor wall. Suppression holes are formed in the combustor wall. The suppression holes are evenly arranged across the wall section, i.e. the suppression holes have the same distance between each other.

  U.S. Patent No. 6,099,077 discloses a combustion chamber for a gas turbine engine, which is a double wall combustion chamber. The inner and outer walls of the double wall combustion chamber are provided with bleed holes to provide impingement cooling. The exudation holes are evenly distributed over the effective inner and outer walls.

  Patent Document 3 discloses an improved inner cylinder in a combustion chamber of a gas turbine. The cooling air can be guided through the opening of each wall of the inner cylinder.

British Patent Application No. 2309296 European Patent Application No. 1104871 European Patent Application No. 1321713

  It is an object of the present invention to provide a combustion chamber that reduces combustion instability and has low emissions.

  This object is solved by a housing for a combustion chamber for a gas turbine, by a combustion chamber for a gas turbine and by a method for manufacturing a combustion chamber for a gas turbine according to the independent claims. The

  In a first aspect of the invention, a housing for a combustion chamber for a gas turbine is presented. The housing includes a wall element having a first hole arrangement and a second hole arrangement. The first hole arrangement includes first holes through which fluid can flow. The first hole portion arrangement further includes a first surface density composed of the first hole portions. The second hole arrangement includes second holes, through which fluid can flow. The second hole portion arrangement further includes a second surface density composed of the second hole portions. The first surface density is different from the second surface density.

  In a further aspect of the invention, a combustion chamber for a gas turbine is presented. The combustion chamber includes an inner housing having the housing characteristics and an outer housing that may have the housing characteristics. The outer wall element of the outer housing at least partially surrounds the inner wall element of the inner housing, so that a gap is formed between the inner wall element and the further outer wall element.

  The terms “inner” and “outer” relate to the relative position, ie the relative position of the inner and outer wall elements with respect to the distance between the wall element and the flame volume in the combustion chamber. The central axis of the combustion chamber can be a line of symmetry of a combustion chamber (such as a cylinder-type combustion chamber) (eg, cylindrically shaped), that is, a line passing through the flame region, or a gas turbine (annular combustion chamber) For example, parallel or coincident with the center line of rotation.

  In a further aspect of the invention, a method for manufacturing a combustion chamber of a gas turbine is presented. According to the method, a first hole arrangement comprising first holes is formed in the inner wall element of the inner housing, through which the fluid can flow, the first hole arrangement is The first surface density comprising the first hole is provided. Further, according to the method, a second hole arrangement comprising second holes in the inner wall element is formed, fluid can flow through the second holes, and the second hole arrangement is A second surface density composed of two holes is provided. The first surface density is different from the second surface density.

  The term “area density” (surface density) defines the number of holes per unit area. For example, when two adjacent hole arrangements have different surface densities, each of the adjacent hole arrangements has a different number of holes. The result is a non-uniform distribution of holes across each hole arrangement.

  Thus, according to the invention, the wall element of the housing for the combustion chamber comprises a first hole arrangement having a first surface density and a second hole arrangement having a second surface density. Thus, the pores of the wall element are particularly adapted to each of the flow characteristics of each of the fluids distributed unevenly and flowing along the wall element.

  The housing for the combustion chamber of the gas turbine may be an inner housing that surrounds the combustion volume of the combustion chamber, for example. The housing may further be an outer housing that partially surrounds the inner housing. Thus, by applying an inner housing and an outer housing, a double-walled or double-walled combustion chamber (ie, a double skin liner) is formed. There is a gap between the inner casing and the outer casing. Fluid flowing along the outer wall element, such as cooling fluid / gas, enters the gap through the first and second holes of the outer wall element for cooling. The fluid flows from the gap through the first and second holes in the inner wall element and into the combustion space of the combustion chamber for cooling.

  The inner wall of the inner skin of the dual skin liner surrounds the combustor volume of the combustion chamber. The outer wall of the outer housing surrounds the inner wall of such a double skin liner so as to form a gap around the inner housing and thus around the combustor volume. As a result, the gap likewise surrounds the combustor volume. The cooling fluid flow flows into the gap through each of the holes in the outer wall. The cooling fluid flow further flows from the gap between the two wall elements through the hole in the inner wall and into the combustor volume of the combustion chamber.

  Thus, some conventional techniques for the combustion chamber distribute the holes in the wall elements of the housing for the combustion chamber uniformly. In the conventional method, the first hole arrangement and the second hole arrangement have one and the same areal density formed by the holes. According to the inventive method of the present invention, the holes are unevenly distributed in the (inner and outer) housings of the combustion chamber. Thereby, the pore distribution is adapted and customized to the (combusted) fluid flow parameters of the combustion chamber and to the cooling gas flow parameters.

  This reduces the combustion dynamics inside the combustion chamber. Thus, a long life of the housing and other combustion components results, for example due to reduced temperature profile variations in the wall elements. In addition, reducing the combustion dynamics of the wall section increases the turbine efficiency and operating temperature of the turbine without affecting the life of the combustion chamber housing. Thus, similarly, for example, by operating the gas turbine with lean burn combustion, that is, by reducing the pilot fuel split inside the gas turbine, reducing nitrogen oxide (NOx) emissions To do. In summary, by distributing the holes in a non-uniform manner, and by placing a predetermined pattern of holes in each of the hole arrangements, for example, to provide more combustion to the combustion process to provide lean burn combustion. As supplied, the combustion chamber operates with low nitrogen oxide (NOx) emissions. In addition, the flame temperature is reduced due to lean burn combustion.

  In a further exemplary form, the wall element is formed to extend at least partially along a circumferential direction about the central axis of the combustion chamber. Generally, the combustion chamber is formed in a cylinder shape (or a cone shape). The central axis forms, for example, an axis of symmetry of the combustion chamber. According to a further exemplary form, the first holes of the first hole arrangement are formed in the wall elements one after the other in the circumferential direction to form at least one first row of first holes. ing.

  In a further exemplary form, the second holes of the second hole arrangement are formed in the wall elements one after the other in the circumferential direction so as to form at least one second row of second holes. . For example, the total number of first holes is equal to the total number of second holes when viewed over the entire circumference, but the surface density of the holes in each row varies between the holes in the first and second rows. Yes.

  According to a further exemplary form, the second holes of the second hole arrangement are formed in the wall element one after the other in the circumferential direction to form at least one second row of second holes. ing. Since the first hole portion of the first hole arrangement has a first surface density different from the second surface density of the second hole portion of the second hole arrangement, the total number of first holes is, for example, It is different from the total number of two holes.

  With respect to the exemplary embodiment comprising a first column and a second column, the total amount in the first column is different from the total amount in the second column. Additionally or alternatively, the total amount of the first holes in the first row is different from the total amount of the second holes in the second row. As a result, a first surface density different from the second surface density, and thus a non-uniform distribution of the first and second holes along the wall element.

  In a further exemplary form, the first holes of the first hole arrangement are formed in the wall element one after the other along the first direction. The first direction is different from the circumferential direction to form at least one further first row of first holes.

  In particular, in a further exemplary form, the first angle between the first direction and the circumferential direction is between about 10 ° and about 80 °, in particular between about 30 ° and about 60 °. Thus, the first hole is arranged in the wall element, so that a further first row extends in a spiral manner along each (eg tubular) wall element.

  In a further exemplary form, the second holes of the second hole arrangement are formed in the wall element one after the other along the second direction. The second direction is different from the circumferential direction and / or the first direction to form at least one further second row of second holes.

  In particular, in a further exemplary form, the second angle between the second direction and the circumferential direction is between about 10 ° and about 80 °, in particular between about 30 ° and about 60 °. With the further first row and the further second row, the first and / or second holes, respectively, are formed one after the other along the first and second directions respectively, so that the further first row and the further second row are Form a spiral (ie spiral) extension around the central axis along the wall element.

  In a method according to a further exemplary embodiment, the outer wall element of the outer housing is arranged with respect to the inner wall element, so that the outer wall element at least partly surrounds the inner wall element and therefore A gap is formed between the element and the outer wall element.

  In a method according to a further exemplary embodiment, a further first hole arrangement is formed in the outer wall element, the further first hole arrangement comprising a further first hole and passing through these further first holes. Thus, additional fluid (eg, cooling fluid / gas) is flowable. The further first hole arrangement comprises a further first surface density consisting of a further first hole. Furthermore, a further second hole arrangement comprising additional second holes is formed in the outer wall element, through which further fluid (eg cooling fluid / gas) can flow, The further second hole arrangement comprises a further second surface density consisting of the second hole. The further first surface density is different from the further second surface density.

  The hole area along the inner and outer walls is distributed over the wall, so that bands or regions of different hole density appear. Distribution criteria depend on flow parameters, which can be, for example, temperature, flow velocity, flow direction, and / or fluid and / or further fluid turbulence.

  Therefore, the arrangement of the first hole and the second hole is designed and formed by the above-described method while considering the flow parameter of each fluid. Thus, there is an improvement in guiding the effective hole distribution of the holes and thus the fluid and further fluid along each of the wall elements. This likewise achieves the efficiency of the combustion chamber due to the matched hole arrangement.

  For example, the holes of the hole arrangement in the wall element are evenly distributed at the beginning of the method and thus have the same area hole density. Next, some of the holes are removed from the existing hole arrangement, thus creating an uneven distribution and uneven hole density between the hole arrangements. Next, for confirmation, it is measured how much the total hole area has been reduced in the flow test. Next, calculate how each hole is machined and placed to obtain a nominal flow parameter to achieve good suppression characteristics. Next, the holes with non-uniform distribution and / or non-uniform surface density are then distributed in order to match each of the holes to each of the hole arrangements, and thus to match each of the calculated nominal flow parameters and total effective flow area for the combustion chamber. Form.

  The invention described above reduces the combustion dynamics of the fuel inside the combustion chamber. That is, the inner wall element and the outer wall element are perforated with holes in a non-uniform and customized manner. Thus, due to the reduced combustion dynamics, lifetimes for the combustion chamber components and downstream turbine stage components are achieved as a result of reduced flame variation and temperature profile. . Furthermore, a low pilot fuel split (pilot fuel / [pilot fuel + main fuel]) due to reduced combustion dynamics is applied, thus reducing NOx waste.

  It should be noted that the forms of the invention have been described with reference to various subject matters. In particular, some aspects have been described with reference to apparatus type claims whereas other aspects have been described with reference to method type claims. However, those skilled in the art will infer from the above description and the following description, unless otherwise noted, in addition to arbitrarily combining features belonging to one type of subject matter, between features associated with different subject matter, particularly device types Any combination between the features of the following claims and the features of the method type claims is to be considered as disclosed herein.

  The above aspects and further aspects of the invention are apparent from the examples of embodiment to be described hereinafter and are explained with reference to the examples of embodiment. The present invention is described in detail below with reference to exemplary embodiments, which, however, do not limit the present invention.

FIG. 3 shows a combustion chamber housing having first and second rows of holes according to an exemplary embodiment of the present invention. FIG. 3 shows a combustion chamber housing having first and second rows of holes according to an exemplary embodiment of the present invention. It is the schematic which shows the hole part pattern in each housing | casing of the combustion chamber concerning illustrative embodiment of this invention. It is the schematic which shows the hole part pattern in each housing | casing of the combustion chamber concerning illustrative embodiment of this invention. FIG. 2 is a schematic diagram showing a combustion chamber with inner and outer housings. FIG. 6 is a schematic diagram illustrating a method for manufacturing a housing according to an exemplary embodiment of the present invention.

  What is shown in the drawings is schematic. It should be noted that similar or identical components are provided with the same reference signs in the various figures.

  FIG. 1 shows a housing for a combustion chamber 100 for a gas turbine. The housing includes a wall element 101 having a first hole arrangement I and a second hole arrangement II. The first hole arrangement I includes first holes 110, and fluid can flow through the first holes 110. The first hole arrangement I includes a first hole 110 having a first surface density.

  The second hole arrangement II includes second holes 120 through which fluid can flow. The second hole arrangement II includes a second hole 120 having a second surface density.

  The first surface density is different from the second surface density. That is, the integration of the first hole 110 per area unit is different from the integration of the second hole 120 per area unit. That is, the first holes 110 are distributed in different patterns and / or different amounts and / or different sizes (for example, hole diameters) with respect to the second holes 120 in the second hole arrangement II. .

  For example, as can be seen from FIG. 1, the first hole arrangement I, the second hole arrangement II, and the third hole arrangement III, for example, have the same surface size. Furthermore, the 1st hole arrangement | positioning I, the 2nd hole arrangement | positioning II, and the 3rd hole arrangement | positioning III prescribe | regulate the area unit which prescribes | regulates each 1st, 2nd and / or 3rd surface density of a hole.

  In FIG. 1, the density of the first hole 110 in the first hole arrangement I is higher than the second surface density and the third surface density in the second hole arrangement II and the third hole arrangement III, respectively. Yes.

  Since the flame is located at the upstream front end, more holes may be arranged at the upstream front end of the wall element 101. For example, as exemplarily shown in FIG. 1, the first hole arrangement I has three first rows 111, and the second hole arrangement II located further downstream has two second rows 121. And the third hole arrangement III located further downstream has one third row 131.

  In particular, as shown in FIG. 1, the combustion chamber 100 includes a combustor section 104 (eg, a front end section) at a location upstream of the combustion chamber 100 with respect to the direction of fluid flow along the central axis 102 of the combustion chamber 100. At the downstream end of the combustion chamber 100 with respect to the direction of fluid flow along the central axis 102, the combustion gas exits the combustion chamber 100 and further flows into the turbine stage of the gas turbine, for example. As can be seen from FIG. 1, the surface density of each hole 110, 120, 130 decreases from the upstream end to the downstream end of the combustion chamber 100. Due to the distribution of the exemplary holes 110, 120, 130 of FIG. 1, the first holes 110 in the first hole arrangement I are arranged in the circumferential direction 103 to form the first holes 110 in the first row 111. Are formed in the wall element 101 one after another. Adjacent to the first row 111 and along the downstream direction, the second hole portions 120 of the second hole arrangement II are successively wall elements to form, for example, the second hole portions 120 of the second row 121. 101. Further, as shown in FIG. 1, the third hole portions 113 of the third hole portion arrangement III are successively wall elements 101 along the circumferential direction to form at least the third hole portions 130 of the third row 131. Is formed.

  For example, if each hole arrangement I, II, III has the same defined area, the amount of holes 110, 120, 130 and the amount of rows 111, 121, 131 are the upstream end of the combustion chamber 100. To the downstream end of the combustion chamber 100. That is, the distance between the second columns 121 is smaller than the distance between the third columns 131, for example. For example, the distance between the first rows 111 at the upstream end of the combustion chamber 100 is half the distance between the third rows 131 in the downstream section of the combustion chamber 100.

  In FIG. 1, as shown in FIG. 1, the hole arrangements I, II, and III are attached to an inner wall element 501 (see FIG. 5) (inner liner). Due to the non-uniform hole distribution along the central axis 102 from the upstream end of the combustion chamber 100 to the downstream end of the combustion chamber 100, the areal density at the downstream portion is at the upstream portion of the combustion chamber. It is lower than the surface density of the hole. Furthermore, accurate exudation cooling is also achieved, especially in the upstream part of the wall element 101, compared to the uniformly arranged hole arrangement. Further, as shown in FIG. 1, accurate suppression characteristics of combustion dynamics in the combustion chamber 100 are achieved by the hole distribution. The arrangement of the axial rows 111, 121, 131 occurs based on a reduction in the effective area of the combustion chamber and the desired flow rate of the cooling fluid through the holes 110, 120, 130 respectively through the inner wall.

  FIG. 2 shows a combustion chamber 100 in which the wall element 101 comprises a first hole arrangement I and a second hole arrangement II. The first hole portions 110 of the first hole portion arrangement I are formed in the wall element 101 one after another along the first direction 201. The first direction 201 is different from the circumferential direction 103 to form at least one further first row 211 of holes 110.

  The second holes 120 of the additional or alternative second hole arrangement II are formed in the wall element 101 one after the other along the second direction 202. The second direction 202 is different from the circumferential direction 103 to form at least one further second row 221 of second holes 120.

  As can be seen from FIG. 2, the further first row 211 comprises, for example, two first holes 110. The further second row 221 comprises, for example, three second holes 120. Accordingly, the surface density 120 of the second hole 120 in the second hole arrangement II is higher than the surface density of the first hole 110 in the first hole arrangement I.

  Furthermore, as shown in FIG. 2, by arranging the holes 110, 120 along the first and second directions, a spiral flow around the central axis 102 along the wall element 101. Form. That is, in FIG. 2, the holes 110 and 120 are arranged in an oblique manner (spiral pattern) with respect to the circumferential direction 103.

  In particular, a housing with a hole pattern as shown in FIG. 2 is applied for an outer housing having an outer wall element 502 (see FIG. 5). In particular, the first and second directions in the further oblique first and second rows 211, 221 are in the same direction as the spiral and spiral movement of the combustion gas inside the combustion chamber 100. Furthermore, two adjacent diagonal further rows 211, 221 may be uniform or non-uniform along the circumferential direction 103, depending on the required flow parameters through each hole 110, 120, 130. Good.

  Combustion chamber 100 comprising the inner housing shown in FIG. 1 and the outer housing shown in FIG. 2 has the surprising effects of effective cooling characteristics, effective flame dynamics suppression, and stable flame characteristics in the combustion chamber.

  FIG. 3 is a more schematic diagram of the hole pattern as shown in FIG. FIG. 3 particularly shows the hole pattern of the outer wall 502 (see FIG. 5) of the outer housing of the combustion chamber 100. FIG. 3 exemplarily shows the first hole arrangement I and the second hole arrangement II. The first holes 110 are arranged one after another along the further first row 211. The further first row 211 extends along the first direction 201. A first angle α1 is defined between the first direction 201 and the circumferential direction 103.

  The second holes 120 are sequentially arranged in the second hole arrangement II along the second direction 202, and form a further second row 221. A second angle α2 is defined between the second direction 202 and the circumferential direction 103.

  As shown in FIG. 3, the further first row 211 and the further second row 221 have a spiral (oblique) spread with respect to the circumferential direction 103. In particular, as shown in FIG. 3, along the circumferential direction 103, the distance between each of the further rows 211, 221 is different from each other. For example, as shown in the first hole arrangement I, the first hole arrangement I comprises three pairs of further first rows 211, and between each pair of further first rows 211, a further first row 211. There is a distance that is longer than the distance between each two additional first rows 211 that define each pair.

  In comparison, as shown in the second hole arrangement II, an additional second row 221 of the second hole arrangement II2 pair and one additional second row arrangement comprising three additional second rows 221. Prepare.

  Thus, along the circumferential direction, the distance between each of the further rows 211, 221 varies to form a non-uniform distribution of the holes 110, 120.

  FIG. 4 is a schematic view of a hole pattern as schematically shown in FIG. In particular, the hole pattern shown in FIG. 4 is beneficial when applied to the inner wall 501 (see FIG. 5) of the inner housing of the combustion chamber 100. The first hole portions 110 in the first row 111 and the second hole portions 120 in the second row 121 are arranged one after another along the axial direction 102, and the first row 111 and the second row 121 are arranged in the circumferential direction. 103 is parallel. The distance between the first rows 111 in the first hole arrangement I is smaller than the distance between the second rows 121 in the second hole arrangement II.

  FIG. 5 shows for a better overall cross section of a double-walled cylinder type combustion chamber 100. The inner wall portion 501 of the inner housing surrounds the combustor volume of the combustion chamber 100. The outer wall 502 of the outer casing surrounds the inner casing so as to form a gap. The cooling fluid flow 503 can flow into the gap through each of the holes 110, 120 in the outer wall 502. The cooling fluid stream 503 forms at least a portion of the cooling fluid stream 504 that flows from the gap between the two wall elements 501, 502 through the holes 110, 120, 130 of the inner wall 501 into the combustion chamber 100. The cooling fluid flow 504 is smaller or larger than the cooling fluid flow 503 depending on whether cooling fluid is added or removed in the gap between the two wall elements 501, 502.

  As shown in FIG. 5, the inner wall 502 and the outer wall 502 surround the central axis 102 and thus form a tubular section of the combustion chamber 100.

  FIG. 6 shows a method of adjusting and arranging the desired hole arrangements I, II, III of the inner wall element 501 and the outer wall element 502. In step 601, an internal combustion chamber design is defined. The internal combustion chamber design comprises a hole pattern that is uniformly or non-uniformly distributed in the inner wall element 501 and / or in the outer wall element 502.

  The combustion chamber is then operated under nominal operating conditions and measured or analyzed so that the inner wall element 501 and the outer wall element 502 are exposed to a cooling fluid stream 503 and a further cooling fluid stream 504, respectively. The cooling fluid has its respective operational flow parameters and flows through each of the holes in the inner wall element 501 and the outer wall element 502.

  Next, in step 602, the hole arrangement I, II, III of the inner wall element 501 is determined. The effective area of the inner wall element 501 is determined from the total number of holes 110, 120, 130 of the inner wall element 501. Similarly, in step 603, the hole arrangements I, II, III of the outer wall element 502 are determined. The effective area of the outer wall element (outer liner) 502 is determined from the total number of holes 120, 130, 140 in the wall of the outer wall element 502.

  Next, in step 605, the total effective area of the combustion chamber 100 is determined based on the hole arrangements I, II, III of the inner wall element 501 and the hole arrangements I, II, III of the outer wall element 502.

  Further, a flow parameter of fluid exiting the inner wall element 501 into the combustion space of the combustion chamber 100 (eg, the velocity of the additional cooling fluid flow 504) is determined (see step 604).

  Next, in step 606, the determined values of the fluid parameters of the cooling fluids 503, 504 and the geometric parameters of the combined inner and outer wall elements 501, 502 are combined, for example, with the velocity of the cooling fluids 503, 504 and the combustion chamber 100. Compare with the nominal value of the effective area.

  If the measured fluid parameters and / or the nominal values of the geometry of the combustion chamber 100 do not correspond to the respective nominal values, in step 607 the first surface of each of the holes in the inner wall element 501 and / or outer wall element 502 Each of the density, further first surface density, second surface density and / or further second surface density, and thus the hole pattern, is individually corrected until the nominal value of the flow / geometry parameter is reached.

  When the nominal value is achieved, the final design of the hole pattern of the inner wall element 501 and outer wall element 502 is achieved (see step 608).

  Thus, as shown in FIG. 6, the above described method achieves a customized and optimized wall pattern of the inner wall element 501 and the outer wall element 502 under the actual operating conditions of the combustion chamber, and therefore Design an optimal fluid flow and effective combustion chamber 100. In the conventional method, the hole pattern is designed and distributed uniformly over a predetermined surface. With this technique, using a repetitive process as shown in FIG. 6 and described above, a hole in a given plane is balanced between the requirement to suppress and the requirement to distribute cooling air over the surface. Determine the pattern. That is, the hole pattern is customized to the operating conditions of the combustion chamber 100 and the gas turbine to which the combustion chamber 100 is attached.

  For the sake of clarity, all of the holes 110, 120, 130 and the rows 111, 121, 131, 211, 221 are identified by their respective reference numbers in the drawings.

  It should be noted that the term “comprising” does not exclude other components or steps and does not exclude the presence of a plurality of “a” or “an”. Moreover, you may combine the component demonstrated in relation to different embodiment. It should also be noted that reference signs in the claims shall not be construed as limiting the scope of the claims.

100 combustion chamber, 102 central axis, 103 circumferential direction, 110 first hole, further first hole, hole, 111 first row, further first row, axial row, row, 120 second hole, further Second hole, hole, 121 second row, further second row, axial row, row, 201 first direction, further first direction, 211 further first row, further row, 221 further second row, second 2 rows, further rows, 501 inner wall element, inner wall portion, 502 outer wall element, outer wall portion, 503 fluid flow, cooling fluid, 504 further fluid flow, cooling fluid, I first hole arrangement, hole arrangement, II Second hole arrangement, hole arrangement, α1 first angle, α2 second angle

Claims (11)

A combustion chamber (100) for a gas turbine, the combustion chamber (100) comprising:
An inner housing and an outer housing;
The inner housing includes an inner wall element (501) having a first hole arrangement (I) and a second hole arrangement (II), and the inner wall element (501) is disposed in the combustion chamber (100). Enclose the combustor volume,
The first hole arrangement (I) includes a first hole (110), fluid can flow through the first hole (110), and the first hole (110) Arranged with a first areal density,
The second hole arrangement (II) includes a second hole (120), fluid can flow through the second hole (120), and the second hole (120) Arranged with a second areal density,
The first surface density is different from the second surface density,
The outer housing comprises an outer wall element (502) comprising a further first hole arrangement (I) and a further second hole arrangement (II);
The outer wall element (502) of the outer housing at least partially surrounds the inner wall element (501) of the inner housing, so that the inner wall element (501) and the outer wall element (502) A gap is formed between
Said further first hole arrangement (I) comprises a further first hole (110) through which the fluid can flow and said further first hole (110) 110) are arranged with a further first areal density,
The further second hole arrangement (II) comprises a further second hole (120) through which the fluid can flow and the further second hole (120) 120) are arranged with a further second areal density,
The combustion chamber, wherein the further first surface density is different from the further second surface density. The inner wall element (501) extends along a circumferential direction (103) about a central axis (102) of the combustion chamber (100) and / or
The combustion chamber of claim 1, wherein the outer wall element (502) extends along a circumferential direction (103) about a central axis (102) of the combustion chamber (100). The inner wall element (501) extends along a circumferential direction (103) about a central axis (102) of the gas turbine, and / or
The combustion chamber of claim 1, wherein the outer wall element (502) extends along a circumferential direction (103) about a central axis (102) of the gas turbine. The circumferential direction (103) for the first hole portion (110) of the first hole portion arrangement (I) to form at least one first row (111) of the first hole portion (110). Along the inner wall element (501) one after the other and / or
In order to form the further first hole (110) of the further first hole arrangement (I) to form at least one further first row (111) of the further first hole (110). 4. Combustion chamber according to claim 2 or 3, characterized in that it is formed in the outer wall element (502) one after the other along the direction (103). The circumferential direction (103) for the second hole portion (120) of the second hole portion arrangement (II) to form at least one second row (121) of the second hole portion (120). Along the inner wall element (501) one after the other and / or
The additional second holes (120) of the additional second hole arrangement (II) form the circumference to form at least one additional second row (121) of the additional second holes (120). The combustion chamber according to any one of claims 2 to 4, characterized in that it is formed in the inner wall element (501) one after another along the direction (103). The first hole portion (110) of the first hole portion arrangement (I) is formed in the inner wall element (501) one after another along a first direction (201),
The first direction (201) differs from the circumferential direction (103) to form the first holes (110) in at least one further first row (211),
The further first hole arrangement (I) of the further first hole arrangement (I) is formed in the outer wall element (502) one after another along a further first direction (201);
6. The method according to claim 2, wherein the further first direction (201) is different from the circumferential direction (103) to form at least one further first row (211). A combustion chamber as described. The first angle (α1) between the first direction (201) and the circumferential direction (103) is between 10 ° and 80 °, in particular between 30 ° and 60 °, and / or
The further first angle (α1) between the further first direction (201) and the circumferential direction (103) is between 10 ° and 80 °, in particular between 30 ° and 60 °, The combustion chamber of claim 6. The second hole portion (120) of the second hole portion arrangement (II) is formed in the inner wall element (501) one after another along the second direction (202),
The second direction (202) differs from the circumferential direction (103) to form at least one further second row (221) of second holes (120);
The further second hole portion (120) of the further second hole arrangement (II) is formed in the outer wall element (502) one after another along a further second direction (202);
The further second direction (202) differs from the circumferential direction (103) to form a further second hole (120) in at least one further second row (221). The combustion chamber according to any one of 2 to 7. The second angle (α2) between the second direction (202) and the circumferential direction (103) is between 10 ° and 80 °, in particular between 30 ° and 60 °, and / or
The further second angle (α2) between the further second direction (202) and the circumferential direction (103) is between 10 ° and 80 °, in particular between 30 ° and 60 °. The combustion chamber of claim 8. A method of manufacturing a combustion chamber (100) for a gas turbine, the method comprising:
Forming a first hole arrangement (I) including a first hole (110) in an inner wall element (501) of an inner housing of the combustion chamber (100), wherein the first hole (110) ) Through which fluid can flow and the first holes (110) are arranged at a first areal density;
Forming a second hole arrangement (II) with a second hole (120) in the inner wall element (501), wherein fluid can flow through the second hole (120). The second holes (120) are arranged at a second surface density;
The first surface density is different from the second surface density,
The inner wall element (501) surrounds a combustor volume of the combustion chamber (100);
An outer wall element (502) of an outer housing of the combustion chamber (100) is positioned with respect to the inner wall element (501) so that the outer wall element (502) at least partially covers the inner wall element (501). Enclosing and thus forming a gap between the inner wall element (501) and the outer wall element (502);
Forming a further first hole arrangement (I) comprising a further first hole (110) in the outer wall element (502), wherein further fluid is passed through the further first hole (110). Flowable and wherein said further first holes (110) are arranged with a further first areal density;
Forming a second second hole arrangement (II) in the outer wall element (502) comprising a second second hole (120), wherein additional fluid is passed through the second second hole (120). Flowable, wherein the further second holes (120) are arranged with a further second areal density;
The further first area density is different from the further second area density;
A method comprising the steps of: Flowing a fluid flow (503) through the first hole arrangement (I) and the second hole arrangement (II);
Flowing further fluid stream (504) through said further first hole arrangement (I) and said further second hole arrangement (II);
Determining flow parameters of the fluid flow (503) and / or the further fluid flow (504);
Measurements of the flow parameter of the fluid flow (503) and / or the geometry parameter of the combustion chamber (100) are adapted to corresponding nominal values of the flow parameter and / or the geometry parameter of the combustion chamber (100). Correcting the first surface density, the further first surface density, the second surface density, and / or the further second surface density until:
The method of claim 10, comprising:

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