EP3245451A1 - Gas turbine combustion chamber having a wall contour - Google Patents

Gas turbine combustion chamber having a wall contour

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Publication number
EP3245451A1
EP3245451A1 EP16822139.8A EP16822139A EP3245451A1 EP 3245451 A1 EP3245451 A1 EP 3245451A1 EP 16822139 A EP16822139 A EP 16822139A EP 3245451 A1 EP3245451 A1 EP 3245451A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
gas turbine
bulges
turbine combustor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP16822139.8A
Other languages
German (de)
French (fr)
Other versions
EP3245451B1 (en
Inventor
Carsten Clemen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3245451A1 publication Critical patent/EP3245451A1/en
Application granted granted Critical
Publication of EP3245451B1 publication Critical patent/EP3245451B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to a gas turbine combustion chamber according to the features of the preamble of claim 1.
  • the invention relates to a gas turbine combustor having an inner combustor wall and an outer combustor wall which form an annular combustor.
  • a gas turbine combustor having an inner combustor wall and an outer combustor wall which form an annular combustor.
  • mixing air holes distributed around the circumference are formed, through which admixing air is introduced into the interior of the combustion chamber.
  • the invention relates to a gas turbine combustor as described in WO 2014/149081 A1.
  • a combustion chamber operates according to the "counter swirl doublet mixer concept.”
  • the combustion chamber which can be modularly constructed with individual modules arranged distributed around the circumference, comprises an outer and an inner combustion chamber wall and a head plate, in which recesses
  • the combustion chamber itself has a single-walled construction, so that the outer combustion chamber wall and the inner combustion chamber wall are made, for example, of formed sheet metal in each case two mixed air holes in pairs next to each other, according to the "counter swirl doublet mixer concept". There are thus provided two mixing holes for each fuel nozzle.
  • the mixing air holes are formed in the prior art so that they are provided with a substantially tubular air guide, which extends relatively far into the interior of the combustion chamber.
  • the problem arises that the air ducts of the mixing air holes are relatively long and, as mentioned, protrude into the interior of the combustion chamber and thus into the flame zone. It is only very conditionally possible to cool the air ducts so that they burn off during operation. By such burnup, however, the temperature distribution changes on Combustion chamber exit considerably. This also leads to increased undesirable NOX emissions.
  • the previously provided for the "counter swirl doublet mixer concept" combustion chambers are only limited use.
  • the invention has for its object to provide a gas turbine combustor of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and allows effective supply of admixed air.
  • the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.
  • the respective combustion chamber wall namely both the inner combustion chamber wall and the outer combustion chamber wall in the region of the mixing air holes is bulged to the interior of the combustion chamber wall, wherein the mixing air hole is arranged in the respective bulge.
  • the solution according to the invention thus provides that, distributed around the circumference, analogous to the distribution of the mixed air holes, viewed from the interior of the combustion chamber, convex bulges are formed. These extend in the region of the respective mixing air hole or the pairwise mixing air holes provided in accordance with the "counter swirl doublet mixer concept.” Thus, tubular air ducts do not extend into the interior of the combustion chamber from the mixing air holes, as provided for in the prior art As the one or more mixing holes are provided in the respective bulge, the admixing air passing through the mixing air hole is reliably guided into the inner portion of the interior of the combustion chamber.
  • a plurality of bulges are thus preferably formed distributed on the circumference, which correspond to the number of mixing air holes or mixed air hole pairs.
  • the result is thus a wave-like contouring of the combustion chamber wall distributed around the inner circumference of the annular combustion chamber in the region of the mixing air holes arranged on the circumference.
  • This contouring is provided both on the inner combustion chamber wall and on the outer combustion chamber wall.
  • the bulge preferably starts axially in front of the or the respective mixing air holes and ends axially behind the mixed air holes.
  • axial in this case refers to the direction of flow through the combustion chamber or to its center axis in the sectional view to be considered in each case, since it is an annular combustion chamber, the central axes to be considered for the individual burners arranged on a truncated cone, as well as the prior art shows. The respective center axes are thus only in an axial section plane parallel to the engine axis.
  • the bulges are arranged offset to each other on the inner combustion chamber wall and the outer combustion chamber wall, based on a radial section plane to follow with the provided in the bulges Misch Kunststofflöchern the "counter swirl doublet mixer concept".
  • the invention is not limited to the "counter swirl doublet mixer concept", but it is also possible to provide only a mixed air hole in a bulge.
  • the mixing air holes are arranged in pairs.
  • the bulges preferably have rounded side surfaces in order to improve the flow behavior through the interior of the combustion chamber. It is particularly advantageous if the bulges, based on the flow direction of the combustion chamber, in each case to the combustion chamber wall have an inflow surface, which forms a smaller angle, as an outflow surface. This also serves for efficient flow guidance through the interior of the combustion chamber.
  • the mixed air holes in particular if they are arranged in pairs, have mutually different diameters.
  • the height of the bulges is preferably between 7.5% and 25% of the total height of the interior of the combustion chamber.
  • cooling air holes in particular effusion holes
  • the bulges according to the invention can be produced by deep drawing or pressing the sheet of the combustion chamber by means of suitable tools in the underlying single-walled, made of sheet metal combustion chamber construction. There are thus local bulges from the outside of the respective combustion chamber wall to the interior of the Burner pressed or introduced by a suitable forming process.
  • the mixing air holes can be formed by milling, laser cutting or the like in the bulges.
  • the additional cooling holes / effusion holes can be created by laser drilling or similar methods.
  • FIG. 1 is a schematic representation of a gas turbine engine according to the present invention
  • FIG. 2 is a simplified axial sectional view of a combustion chamber according to the prior art
  • Fig. 3 is a view, analogous to FIG. 2, in a radial section plane according to the prior
  • Fig. 4 is a simplified sectional view of an inventive
  • Fig. 5 is a radial sectional view of the embodiment of FIG. 4 in
  • FIG. 6 is an axial sectional view along section line A of Fig. 5,
  • FIG. 7 is a view, analogous to FIG. 6, according to section line B of FIG. 5, FIG.
  • Fig. 8 is a schematic interior view of a portion of the combustion chamber wall
  • Fig. 9 is a sectional view, analogous to FIG. 4, showing a manufacturing possibility
  • FIG. 10 is a sectional view, analogous to FIG. 5.
  • the gas turbine engine 10 of FIG. 1 is a generally illustrated example of a turbomachine to which the invention may find application.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 1 1, a circulating in a housing fan 12, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, all of which are arranged about a central engine axis 1.
  • the medium-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending fixed fixed Guide vanes 20, which are generally referred to as stator blades and project radially inwardly from the core engine housing 21 in an annular flow channel through the compressors 13, 14.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine rotor blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 disposed thereon and the turbine rotor hub 27 and the turbine rotor blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • FIG. 2 is a simplified axial sectional view showing an annular combustion chamber having an inner combustion chamber wall 2 and an outer combustion chamber wall 1 and provided with a head plate 29 in which recesses 30 are formed around the circumference (see Fig. 3), which serve to receive fuel nozzles 31, as is known from the prior art.
  • FIGS. 2 and 3 show, in the axial-sectional plane or radial-sectional plane (FIG. 3), a plurality of mixing air holes 4 distributed around the circumference, which serve for supplying mixed air into an interior 5 of the combustion chamber.
  • the mixing air holes 4 are provided with air ducts 32, which project like a tube into the interior 5, as shown in particular in Fig. 2.
  • the reference numeral 33 a combustion chamber head is shown.
  • the reference numeral 34 denotes an outer casing in which the combustion chamber is arranged.
  • Both the inner combustion chamber wall 2 and the outer combustion chamber wall 3 are provided with cooling air holes 25 which serve as Effusionskühllöcher.
  • the respective air ducts 32 are far in the interior 5 of the combustion chamber and are therefore liable to burn.
  • FIG. 4 shows a sectional view analogous to FIG. 2.
  • the through-flow direction 7 is shown with an arrow. It returns the main flow through the fuel nozzle 31.
  • bulges 6 are provided both on the inner combustion chamber wall 2 and on the outer combustion chamber wall 3, which bulges, viewed from the inner space 5, are convex and have rounded contours.
  • the total height H of the combustion chamber is shown in FIG. 4 and depicts the respective height of the inner space 5 between the inner combustion chamber wall 2 and the outer combustion chamber wall 3.
  • the height h of the bulges 6 is also indicated in FIG. 4. It is between 7.5% and 25% of the total height H.
  • FIG. 5 shows a view C according to FIG. 6 and thus a view from the outflow side of the combustion chamber in a radial section plane.
  • the recesses 30 are shown for the fuel nozzles 31.
  • Both the inner combustion chamber wall 2 and the outer combustion chamber wall 3 are distributed around the circumference in the region of the mixing air holes 4 with bulges 6 which extend into the interior 5 of the combustion chamber and thus in the sectional view leads to a wave-shaped contour of the combustion chamber walls 2, 3 ,
  • FIG. 5 shows a simplified representation of tools 35, which are explained in more detail below in conjunction with FIGS. 9 and 10. These tools 35 serve to produce the bulges 6.
  • FIG. 5 shows two sections A and B arranged in the radial direction. Sectional views along these sections A and B are shown in FIGS. 6 and 7.
  • 6 shows a view according to section line A and illustrates the shape and arrangement of the bulges 6. These have an inflow surface 8 and an outflow surface 9 in the throughflow direction 7 (see FIG. It can be seen that the inflow surface 8 is arranged at a shallower angle to the respective combustion chamber wall 2, 3 than the outflow surface 9. This is also illustrated once more in the view of FIG. 8. It can be seen that the bulges 6 need not be circular. The geometry depends on the dimensioning and design of the combustion chamber. Also provided in the respective bulge 6 mixing air holes 4 may be provided with different diameters, analogous to the representation in Fig. 3 and the "counter swirl doublet mixer concept".
  • the walls of the bulge 6 are provided with cooling air holes 25.
  • FIGS. 5 to 7 show that in the region of the mixed air holes, which are located in a central region of the cross section of the annular combustion chamber, alternately the inner combustion chamber wall 2 and the outer combustion chamber wall 3, matching the alternating arrangement of the mixed air holes (see Fig. 3), the bulges 6 according to the invention are provided. These may be dimensioned differently on the inner combustion chamber wall 2 and on the outer combustion chamber wall 3. The height h and thus the penetration depth of the bulges are preferably selected so that the admixing air entering through the mixing air holes 4 is discharged in the same way as in the prior art (see FIG. 3), in which additional tubular air ducts 32 are provided.
  • FIGS. 9 and 10 show, as already indicated in FIG. 5, possibilities for producing the bulges 6 according to the invention.
  • These can be pressed in from outside by suitable tools 35, which act similarly to a deep-drawing tool.
  • suitable tools 35 which act similarly to a deep-drawing tool.
  • the impressing from the outside tools can have a suitably selected shape to the contour of the bulges 6, which results, for example, from FIG. 8.
  • the cooling air holes 25 are then formed, for example by laser drilling or the like, while the mixing air holes 4, for example by laser cutting, can be generated.
  • the radii of the recesses are, for example, 10 to 15 mm in order not to impair the component strength and to allow production by the tools 35. These radii also determine the beginning and the end of the respective bulges both in the axial direction and in the circumferential direction.
  • the bulge 6 is provided with an inflow surface 8 and an outflow surface 9.
  • the mixing air holes 4 may be formed in the inflow surface 8, it is also possible to provide these at the apex of the respective bulge 6.
  • the bulges 6 are, compared to the positions on the inner combustion chamber wall 2 and the outer combustion chamber wall 3, circumferentially offset from each other to supply mixing air according to the "counter swirl doublet mixer concept", as shown in simplified in Fig. 3.
  • the bulges 6 can be formed both symmetrically and asymmetrically, both in the axial direction and in the radial direction. This makes it possible to optimize the flow conditions in the interior 5 of the combustion chamber and to adapt the "counter swirl doublet mixer concept". Overall, this results in a staggered arrangement, as explained for example in FIGS. 5 and 10.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a gas turbine combustion chamber comprising an inner combustion chamber wall (2) and an outer combustion chamber wall (3) that form an annular combustion chamber; air blending holes (4) are distributed along the circumference of the inner (2) and outer combustion chamber walls (3); in the region of said air blending holes (4), the combustion chamber walls (2, 3) bulge in the direction of the interior (5) of the combustion chamber (15), the air blending hole (4) being located in the bulge (6).

Description

Gasturbinenbrennkammer mit Wandkonturierung  Gas turbine combustor with wall contouring
Beschreibung Die Erfindung bezieht sich auf eine Gasturbinenbrennkammer gemäß den Merkmalen des Oberbegriffs des Anspruchs 1 . The invention relates to a gas turbine combustion chamber according to the features of the preamble of claim 1.
Im Einzelnen bezieht sich die Erfindung auf eine Gasturbinenbrennkammer mit einer inneren Brennkammerwand und einer äußeren Brennkammerwand, welche eine Ringbrennkammer bilden. In der inneren Brennkammerwand und in der äußeren Brennkammerwand sind um den Umfang verteilt Mischluftlöcher ausgebildet, durch welche Zumischluft in den Innenraum der Brennkammer eingeleitet wird. In particular, the invention relates to a gas turbine combustor having an inner combustor wall and an outer combustor wall which form an annular combustor. In the inner combustion chamber wall and in the outer combustion chamber wall, mixing air holes distributed around the circumference are formed, through which admixing air is introduced into the interior of the combustion chamber.
Im speziellen betrifft die Erfindung eine Gasturbinenbrennkammer, so wie diese in der WO 2014/149081 A1 beschrieben ist. Eine derartige Brennkammer arbeitet nach dem„counter swirl doublet mischer concept". Die Brennkammer, welche in Modulbauweise mit einzelnen, um den Umfang verteilt angeordneten, miteinander verbundenen Modulen aufgebaut sein kann, umfasst eine äußere und eine innere Brennkammerwand sowie eine Kopfplatte, in der Aussparungen vorgesehen sind, durch welche Treibstoffdüsen den Brennraum erreichen können. Die Brennkammer selbst ist einwandig ausgebildet, so dass die äußere Brennkammerwand und die innere Brennkammerwand beispielsweise aus geformtem Blech hergestellt sind. Um den Umfang verteilt sind Mischluftlöcher vorgesehen, durch welche Zumischluft zugeführt wird. Dabei befinden sich jeweils zwei Mischluftlöcher paarweise direkt nebeneinander, gemäß dem „counter swirl doublet mischer concept". Es sind somit zwei Mischluftlöcher pro Treibstoffdüse vorgesehen. Die Mischluftlöcher sind nach dem Stand der Technik so ausgebildet, dass sie mit einer im Wesentlichen rohrartigen Luftführung versehen sind, die sich relativ weit in den Innenraum der Brennkammer erstreckt. Dabei tritt das Problem auf, dass die Luftführungen der Mischluftlöcher relativ lang sind und, wie erwähnt, in den Innenraum der Brennkammer und damit in die Flammenzone vorstehen. Es ist dabei nur sehr bedingt möglich, die Luftführungen zu kühlen, so dass diese während des Betriebs abbrennen. Durch einen derartigen Abbrand ändert sich jedoch die Temperaturverteilung am Brennkammeraustritt erheblich. Dies führt auch zu gesteigerten unerwünschten NOX- Emissionen. Somit sind die bisher zu dem „counter swirl doublet mischer concept" vorgesehenen Brennkammern nur eingeschränkt einsetzbar. In particular, the invention relates to a gas turbine combustor as described in WO 2014/149081 A1. Such a combustion chamber operates according to the "counter swirl doublet mixer concept." The combustion chamber, which can be modularly constructed with individual modules arranged distributed around the circumference, comprises an outer and an inner combustion chamber wall and a head plate, in which recesses The combustion chamber itself has a single-walled construction, so that the outer combustion chamber wall and the inner combustion chamber wall are made, for example, of formed sheet metal in each case two mixed air holes in pairs next to each other, according to the "counter swirl doublet mixer concept". There are thus provided two mixing holes for each fuel nozzle. The mixing air holes are formed in the prior art so that they are provided with a substantially tubular air guide, which extends relatively far into the interior of the combustion chamber. The problem arises that the air ducts of the mixing air holes are relatively long and, as mentioned, protrude into the interior of the combustion chamber and thus into the flame zone. It is only very conditionally possible to cool the air ducts so that they burn off during operation. By such burnup, however, the temperature distribution changes on Combustion chamber exit considerably. This also leads to increased undesirable NOX emissions. Thus, the previously provided for the "counter swirl doublet mixer concept" combustion chambers are only limited use.
Der Erfindung liegt die Aufgabe zugrunde, eine Gasturbinenbrennkammer der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit die Nachteile des Standes der Technik vermeidet und eine effektive Zuführung von Zumischluft ermöglicht. The invention has for its object to provide a gas turbine combustor of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and allows effective supply of admixed air.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung. Erfindungsgemäß ist somit vorgesehen, dass die jeweilige Brennkammerwand, nämlich sowohl die innere Brennkammerwand als auch die äußere Brennkammerwand im Bereich der Mischluftlöcher zum Innenraum der Brennkammerwand ausgebaucht ist, wobei das Mischluftloch in der jeweiligen Ausbauchung angeordnet ist. 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 respective combustion chamber wall, namely both the inner combustion chamber wall and the outer combustion chamber wall in the region of the mixing air holes is bulged to the interior of the combustion chamber wall, wherein the mixing air hole is arranged in the respective bulge.
Die erfindungsgemäße Lösung sieht somit vor, dass um den Umfang verteilt, analog zu der Verteilung der Mischluftlöcher, vom Innenraum der Brennkammer aus gesehen, konvexe Ausbauchungen ausgebildet sind. Diese erstrecken sich im Bereich des jeweiligen Mischluftlochs bzw. der nach dem „counter swirl doublet mischer concept" vorgesehenen paarweisen Mischluftlöcher. Somit erstrecken sich von den Mischluftlöchern nicht, wie beim Stand der Technik vorgesehen, rohrförmige Luftführungen in den Innenraum der Brennkammer. Vielmehr ist die Brennkammerwand selbst zum Innenraum hin lokal ausgebaucht. Da das oder die Mischluftlöcher in der jeweiligen Ausbauchung vorgesehen ist/sind, wird die durch das Mischluftloch austretende Zumischluft zuverlässig in den inneren Bereich des Innenraums der Brennkammer geleitet. The solution according to the invention thus provides that, distributed around the circumference, analogous to the distribution of the mixed air holes, viewed from the interior of the combustion chamber, convex bulges are formed. These extend in the region of the respective mixing air hole or the pairwise mixing air holes provided in accordance with the "counter swirl doublet mixer concept." Thus, tubular air ducts do not extend into the interior of the combustion chamber from the mixing air holes, as provided for in the prior art As the one or more mixing holes are provided in the respective bulge, the admixing air passing through the mixing air hole is reliably guided into the inner portion of the interior of the combustion chamber.
Erfindungsgemäß sind somit bevorzugterweise am Umfang verteilt mehrere Ausbauchungen ausgebildet, welche der Zahl der Mischluftlöcher oder Mischluftloch-Paare entsprechen. Es ergibt sich somit um den Innenumfang der Ringbrennkammer verteilt im Bereich der am Umfang angeordneten Mischluftlöcher eine wellenartige Konturierung der Brennkammerwand. Diese Konturierung ist sowohl an der inneren Brennkammerwand als auch an der äußeren Brennkammerwand vorgesehen. Die Ausbauchung beginnt erfindungsgemäß bevorzugterweise axial vor dem oder den jeweiligen Mischluftlöchern und endet axial hinter den Mischluftlöchern. Der Begriff „axial" bezieht sich dabei in der jeweils zu betrachtenden Schnittansicht auf die Durchströmungsrichtung der Brennkammer bzw. auf deren Mittelachse. Da es sich um eine Ringbrennkammer handelt, sind die für die einzelnen Brenner zu betrachtenden Mittelachsen auf einem Kegelstumpf angeordnet, so wie dies auch der Stand der Technik zeigt. Die jeweiligen Mittelachsen sind somit nur in einer Axialschnittebene parallel zur Triebwerksachse. According to the invention, a plurality of bulges are thus preferably formed distributed on the circumference, which correspond to the number of mixing air holes or mixed air hole pairs. The result is thus a wave-like contouring of the combustion chamber wall distributed around the inner circumference of the annular combustion chamber in the region of the mixing air holes arranged on the circumference. This contouring is provided both on the inner combustion chamber wall and on the outer combustion chamber wall. According to the invention, the bulge preferably starts axially in front of the or the respective mixing air holes and ends axially behind the mixed air holes. The term "axial" in this case refers to the direction of flow through the combustion chamber or to its center axis in the sectional view to be considered in each case, since it is an annular combustion chamber, the central axes to be considered for the individual burners arranged on a truncated cone, as well as the prior art shows. The respective center axes are thus only in an axial section plane parallel to the engine axis.
In besonders günstiger Weiterbildung der Erfindung ist vorgesehen, dass die Ausbauchungen an der inneren Brennkammerwand und an der äußeren Brennkammerwand zueinander versetzt angeordnet sind, bezogen auf eine Radialschnittebene, um mit den in den Ausbauchungen vorgesehenen Mischluftlöchern dem„counter swirl doublet mischer concept" zu folgen. In a particularly favorable development of the invention it is provided that the bulges are arranged offset to each other on the inner combustion chamber wall and the outer combustion chamber wall, based on a radial section plane to follow with the provided in the bulges Mischluftlöchern the "counter swirl doublet mixer concept".
Wie erwähnt, ist die Erfindung nicht auf das „counter swirl doublet mischer concept" beschränkt, vielmehr ist es auch möglich, in einer Ausbauchung nur ein Mischluftloch vorzusehen. Nach dem „counter swirl doublet mischer concept" sind die Mischluftlöcher hingegen paarweise angeordnet. As mentioned, the invention is not limited to the "counter swirl doublet mixer concept", but it is also possible to provide only a mixed air hole in a bulge.According to the "counter swirl doublet mixer concept", the mixing air holes are arranged in pairs.
Die Ausbauchungen weisen bevorzugterweise gerundete Seitenflächen auf, um das Strömungsverhalten durch den Innenraum der Brennkammer zu verbessern. Dabei ist es insbesondere vorteilhaft, wenn die Ausbauchungen, bezogen auf die Durchströmungsrichtung der Brennkammer, jeweils zur Brennkammerwand eine Anströmfläche aufweisen, welche einen kleineren Winkel ausbildet, als eine Abströmfläche. Auch dies dient zur effizienten Strömungsführung durch den Innenraum der Brennkammer. The bulges preferably have rounded side surfaces in order to improve the flow behavior through the interior of the combustion chamber. It is particularly advantageous if the bulges, based on the flow direction of the combustion chamber, in each case to the combustion chamber wall have an inflow surface, which forms a smaller angle, as an outflow surface. This also serves for efficient flow guidance through the interior of the combustion chamber.
Die Mischluftlöcher können, insbesondere wenn sie paarweise angeordnet sind, zueinander unterschiedliche Durchmesser aufweisen. The mixed air holes, in particular if they are arranged in pairs, have mutually different diameters.
Besonders vorteilhaft ist es, wenn das jeweilige Mischluftluch an einer Anströmfläche der Ausbauchung vorgesehen ist. Auch hierdurch wird die Strömungsführung in Zusammenhang mit einer verbesserten Einleitung von Zumischluft optimiert. It when the respective Mischluftluch is provided on an inflow surface of the bulge is particularly advantageous. This also optimizes the flow guidance in connection with an improved introduction of admixed air.
Die Höhe der Ausbauchungen beträgt bevorzugterweise zwischen 7,5% und 25% der gesamten Höhe des Innenraums der Brennkammer. The height of the bulges is preferably between 7.5% and 25% of the total height of the interior of the combustion chamber.
Um die Kühlung der Brennkammerwand zu verbessern, kann es vorteilhaft sein, in der Wandung der Ausbauchungen Kühlluftlöcher, insbesondere Effusionslöcher, vorzusehen. Durch diese wird Kühlluft ausgeleitet, welche zur Kühlung der äußeren bzw. der inneren Brennkammerwand dient. Die erfindungsgemäßen Ausbauchungen können bei der zugrundeliegenden einwandigen, aus Blech gefertigten Brennkammerkonstruktion durch Tiefziehen oder Drücken des Blechs der Brennkammer mittels geeigneter Werkzeuge erzeugt werden. Es werden somit lokale Ausbauchungen von der Außenseite der jeweiligen Brennkammerwand zum Innenraum der Brennkammer eingedrückt oder durch ein geeignetes Umformverfahren eingebracht. Die Mischluftlöcher können durch Fräsen, Laserschneiden oder Ähnliches in den Ausbauchungen ausgebildet werden. Die zusätzlichen Kühlluftlöcher/Effusionslöcher können durch Laserbohren oder ähnliche Verfahren erzeugt werden. Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt: In order to improve the cooling of the combustion chamber wall, it may be advantageous to provide cooling air holes, in particular effusion holes, in the wall of the bulges. By this cooling air is discharged, which serves to cool the outer and the inner combustion chamber wall. The bulges according to the invention can be produced by deep drawing or pressing the sheet of the combustion chamber by means of suitable tools in the underlying single-walled, made of sheet metal combustion chamber construction. There are thus local bulges from the outside of the respective combustion chamber wall to the interior of the Burner pressed or introduced by a suitable forming process. The mixing air holes can be formed by milling, laser cutting or the like in the bulges. The additional cooling holes / effusion holes can be created by laser drilling or similar methods. In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:
Fig. 1 eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung, 1 is a schematic representation of a gas turbine engine according to the present invention,
Fig. 2 eine vereinfachte Axialschnittansicht einer Brennkammer gemäß dem Stand der Technik, 2 is a simplified axial sectional view of a combustion chamber according to the prior art,
Fig. 3 eine Ansicht, analog Fig. 2, in einer Radialschnittebene gemäß dem Stand der Fig. 3 is a view, analogous to FIG. 2, in a radial section plane according to the prior
Technik,  Technology,
Fig. 4 eine vereinfachte Schnittansicht eines erfindungsgemäßen Fig. 4 is a simplified sectional view of an inventive
Ausführungsbeispiels, analog Fig. 2, Fig. 5 eine Radialschnittansicht des Ausführungsbeispiels gemäß Fig. 4 in  Embodiment, analogous to Fig. 2, Fig. 5 is a radial sectional view of the embodiment of FIG. 4 in
Darstellung, analog Fig. 3,  Representation, analogous to FIG. 3,
Fig. 6 eine Axialschnittansicht gemäß Schnittlinie A von Fig. 5, 6 is an axial sectional view along section line A of Fig. 5,
Fig. 7 eine Ansicht, analog Fig. 6, gemäß Schnittlinie B von Fig. 5, 7 is a view, analogous to FIG. 6, according to section line B of FIG. 5, FIG.
Fig. 8 eine schematische Innenansicht eines Teilbereichs der Brennkammerwand, Fig. 9 eine Schnittansicht, analog Fig. 4, mit Darstellung einer Fertigungsmöglichkeit, und Fig. 8 is a schematic interior view of a portion of the combustion chamber wall, Fig. 9 is a sectional view, analogous to FIG. 4, showing a manufacturing possibility, and
Fig. 10 eine Schnittansicht, analog Fig. 5. 10 is a sectional view, analogous to FIG. 5.
Das Gasturbinentriebwerk 10 gemäß Fig. 1 ist ein allgemein dargestelltes Beispiel einer Turbomaschine, bei der die Erfindung Anwendung finden kann. Das Triebwerk 10 ist in herkömmlicher Weise ausgebildet und umfasst in Strömungsrichtung hintereinander einen Lufteinlass 1 1 , einen in einem Gehäuse umlaufenden Fan 12, einen Mitteldruckkompressor 13, einen Hochdruckkompressor 14, eine Brennkammer 15, eine Hochdruckturbine 16, eine Mitteldruckturbine 17 und eine Niederdruckturbine 18 sowie eine Abgasdüse 19, die sämtlich um eine zentrale Triebwerksachse 1 angeordnet sind. Der Mitteldruckkompressor 13 und der Hochdruckkompressor 14 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 20 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Kerntriebwerksgehäuse 21 in einen ringförmigen Strömungskanal durch die Kompressoren 13, 14 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 22 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 26 vorstehen, die mit Naben 27 der Hochdruckturbine 16 bzw. der Mitteldruckturbine 17 gekoppelt sind. The gas turbine engine 10 of FIG. 1 is a generally illustrated example of a turbomachine to which the invention may find application. The engine 10 is formed in a conventional manner and comprises in succession an air inlet 1 1, a circulating in a housing fan 12, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, all of which are arranged about a central engine axis 1. The medium-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending fixed fixed Guide vanes 20, which are generally referred to as stator blades and project radially inwardly from the core engine housing 21 in an annular flow channel through the compressors 13, 14. The compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
Die Turbinenabschnitte 16, 17, 18 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 23, die radial nach innen vom Gehäuse 21 in den ringförmigen Strömungskanal durch die Turbinen 16, 17, 18 vorstehen, und eine nachfolgende Anordnung von Turbinenrotorschaufeln 24, die nach außen von einer drehbaren Nabe 27 vorstehen. Die Kompressortrommel oder Kompressorscheibe 26 und die darauf angeordneten Schaufeln 22 sowie die Turbinenrotornabe 27 und die darauf angeordneten Turbinenrotorschaufeln 24 drehen sich im Betrieb um die Triebwerksachse 1 . The turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine rotor blades 24 projecting outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the blades 22 disposed thereon and the turbine rotor hub 27 and the turbine rotor blades 24 disposed thereon rotate about the engine axis 1 during operation.
Die Fig. 2 und 3 zeigen jeweils Brennkammerkonstruktionen gemäß dem „counter swirl doublet mischer concept" nach dem Stand der Technik. Die Fig. 2 zeigt eine Axialschnittansicht in vereinfachter Darstellung. Dabei ist eine Ringbrennkammer gezeigt, welche eine innere Brennkammerwand 2 und eine äußere Brennkammerwand 1 aufweist und mit einer Kopfplatte 29 versehen ist, in welcher um den Umfang verteilt (s. Fig. 3) Aussparungen 30 ausgebildet sind. Diese dienen zur Aufnahme von Treibstoffdüsen 31 , so wie dies aus dem Stand der Technik bekannt ist. 2 and 3 each show combustion chamber constructions according to the prior art "counter swirl doublet mixer concept." Fig. 2 is a simplified axial sectional view showing an annular combustion chamber having an inner combustion chamber wall 2 and an outer combustion chamber wall 1 and provided with a head plate 29 in which recesses 30 are formed around the circumference (see Fig. 3), which serve to receive fuel nozzles 31, as is known from the prior art.
Weiterhin zeigen die Fig. 2 und 3 in Axialschnittebene bzw. Radialschnittebene (Fig. 3) mehrere um den Umfang verteilt angeordnete Mischluftlöcher 4, welche zur Zuführung von Mischluft in einen Innenraum 5 der Brennkammer dienen. Die Mischluftlöcher 4 sind mit Luftführungen 32 versehen, welche rohrartig in den Innenraum 5 vorstehen, so wie dies insbesondere in Fig. 2 dargestellt ist. Furthermore, FIGS. 2 and 3 show, in the axial-sectional plane or radial-sectional plane (FIG. 3), a plurality of mixing air holes 4 distributed around the circumference, which serve for supplying mixed air into an interior 5 of the combustion chamber. The mixing air holes 4 are provided with air ducts 32, which project like a tube into the interior 5, as shown in particular in Fig. 2.
Mit dem Bezugszeichen 33 ist ein Brennkammerkopf dargestellt. Das Bezugszeichen 34 bezeichnet ein Außengehäuse, in welchem die Brennkammer angeordnet ist. Sowohl die innere Brennkammerwand 2 als auch die äußere Brennkammerwand 3 sind mit Kühlluftlöchern 25 versehen, welche als Effusionskühllöcher dienen. Wie sich aus den Fig. 2 und 3 ergibt, stehen die jeweiligen Luftführungen 32 weit in den Innenraum 5 der Brennkammer vor und sind deshalb abbrandgefährdet. The reference numeral 33, a combustion chamber head is shown. The reference numeral 34 denotes an outer casing in which the combustion chamber is arranged. Both the inner combustion chamber wall 2 and the outer combustion chamber wall 3 are provided with cooling air holes 25 which serve as Effusionskühllöcher. As is apparent from Figs. 2 and 3, the respective air ducts 32 are far in the interior 5 of the combustion chamber and are therefore liable to burn.
In den Fig. 4 bis 10 ist ein Ausführungsbeispiel der Erfindung erläutert. Dabei sind gleiche Teile wie in den Fig. 2 und 3 mit gleichen Bezugsziffern versehen, so dass auf eine nochmalige Beschreibung verzichtet werden kann. Die Fig. 4 zeigt eine Schnittansicht analog Fig. 2. Dabei ist die Durchströmungsrichtung 7 mit einem Pfeil dargestellt. Sie gibt die Hauptströmung durch die Treibstoffdüse 31 wieder. In Figs. 4 to 10 an embodiment of the invention is explained. The same parts as in Figs. 2 and 3 are provided with the same reference numerals, so that can be dispensed with a repeated description. 4 shows a sectional view analogous to FIG. 2. In this case, the through-flow direction 7 is shown with an arrow. It returns the main flow through the fuel nozzle 31.
Wie nachfolgend im Einzelnen beschrieben werden wird, sind sowohl an der inneren Brennkammerwand 2 als auch an der äußeren Brennkammerwand 3 Ausbauchungen 6 vorgesehen, welche, von dem Innenraum 5 aus gesehen, konvex ausgebildet sind und abgerundete Konturen aufweisen. Die Gesamthöhe H der Brennkammer ergibt sich aus Fig. 4 und bildet die jeweilige Höhe des Innenraums 5 zwischen der inneren Brennkammerwand 2 und der äußeren Brennkammerwand 3 ab. Die Höhe h der Ausbauchungen 6 ist in Fig. 4 ebenfalls angegeben. Sie beträgt zwischen 7,5% und 25% der Gesamthöhe H. Die Fig. 5 zeigt eine Ansicht C gemäß Fig. 6 und somit eine Ansicht von der Abströmseite der Brennkammer in einer Radialschnittebene. Dabei sind die Aussparungen 30 für die Treibstoffdüsen 31 dargestellt. Sowohl die innere Brennkammerwand 2 als auch die äußere Brennkammerwand 3 ist um den Umfang verteilt im Bereich der Mischluftlöcher 4 mit Ausbauchungen 6 versehen, welche sich in den Innenraum 5 der Brennkammer erstrecken und somit in der Schnittansicht zu einer wellenförmigen Kontur der Brennkammerwände 2, 3 führt. As will be described in detail below, bulges 6 are provided both on the inner combustion chamber wall 2 and on the outer combustion chamber wall 3, which bulges, viewed from the inner space 5, are convex and have rounded contours. The total height H of the combustion chamber is shown in FIG. 4 and depicts the respective height of the inner space 5 between the inner combustion chamber wall 2 and the outer combustion chamber wall 3. The height h of the bulges 6 is also indicated in FIG. 4. It is between 7.5% and 25% of the total height H. FIG. 5 shows a view C according to FIG. 6 and thus a view from the outflow side of the combustion chamber in a radial section plane. The recesses 30 are shown for the fuel nozzles 31. Both the inner combustion chamber wall 2 and the outer combustion chamber wall 3 are distributed around the circumference in the region of the mixing air holes 4 with bulges 6 which extend into the interior 5 of the combustion chamber and thus in the sectional view leads to a wave-shaped contour of the combustion chamber walls 2, 3 ,
Die Fig. 5 zeigt in vereinfachter Darstellung Werkzeuge 35, welche nachfolgend in Verbindung mit den Fig. 9 und 10 näher erläutert werden. Diese Werkzeuge 35 dienen zur Herstellung der Ausbauchungen 6. Die Fig. 5 zeigt zwei in radialer Richtung angeordnete Schnittlinien A und B. Schnittansichten längs dieser Schnittlinien A und B sind in den Fig. 6 und 7 dargestellt. Die Fig. 6 zeigt eine Ansicht gemäß Schnittlinie A und verdeutlicht die Form und Anordnung der Ausbauchungen 6. Diese weisen in Durchströmungsrichtung 7 (s. Fig. 4) eine Anströmfläche 8 sowie eine Abströmfläche 9 auf. Es ist ersichtlich, dass die Anströmfläche 8 in einem flacheren Winkel zur jeweiligen Brennkammerwand 2, 3 angeordnet ist, als die Abströmfläche 9. Dies ist auch nochmals in der Ansicht der Fig. 8 verdeutlicht. Dabei ist zu sehen, dass die Ausbauchungen 6 nicht kreisförmig sein müssen. Die Geometrie richtet sich nach der Dimensionierung und Bauart der Brennkammer. Auch die in der jeweiligen Ausbauchung 6 vorgesehenen Mischluftlöcher 4 können mit unterschiedlichen Durchmessern versehen sein, analog der Darstellung in Fig. 3 und dem„counter swirl doublet mischer concept". 5 shows a simplified representation of tools 35, which are explained in more detail below in conjunction with FIGS. 9 and 10. These tools 35 serve to produce the bulges 6. FIG. 5 shows two sections A and B arranged in the radial direction. Sectional views along these sections A and B are shown in FIGS. 6 and 7. 6 shows a view according to section line A and illustrates the shape and arrangement of the bulges 6. These have an inflow surface 8 and an outflow surface 9 in the throughflow direction 7 (see FIG. It can be seen that the inflow surface 8 is arranged at a shallower angle to the respective combustion chamber wall 2, 3 than the outflow surface 9. This is also illustrated once more in the view of FIG. 8. It can be seen that the bulges 6 need not be circular. The geometry depends on the dimensioning and design of the combustion chamber. Also provided in the respective bulge 6 mixing air holes 4 may be provided with different diameters, analogous to the representation in Fig. 3 and the "counter swirl doublet mixer concept".
Wie in den Fig. 6 und 7 dargestellt, sind die Wandungen der Ausbauchung 6 mit Kühlluftlöchern 25 versehen. As shown in Figs. 6 and 7, the walls of the bulge 6 are provided with cooling air holes 25.
Eine Zusammenschau der Fig. 5 bis 7 zeigt, dass im Bereich der Mischluftlöcher, welche sich in einem mittleren Bereich des Querschnitts der Ringbrennkammer befinden, alternierend an der inneren Brennkammerwand 2 und der äußeren Brennkammerwand 3, passend zu der alternierenden Anordnung der Mischluftlöcher (s. Fig. 3) die erfindungsgemäßen Ausbauchungen 6 vorgesehen sind. Diese können an der inneren Brennkammerwand 2 und an der äußeren Brennkammerwand 3 unterschiedlich dimensioniert sein. Die Höhe h und damit die Eindringtiefe der Ausbauchungen sind bevorzugterweise so gewählt, dass die durch die Mischluftlöcher 4 eintretende Zumischluft in gleicher Weise ausgeleitet wird, wie beim Stand der Technik (s. Fig. 3), bei welchem zusätzliche rohrartige Luftführungen 32 vorgesehen sind. A comparison of FIGS. 5 to 7 shows that in the region of the mixed air holes, which are located in a central region of the cross section of the annular combustion chamber, alternately the inner combustion chamber wall 2 and the outer combustion chamber wall 3, matching the alternating arrangement of the mixed air holes (see Fig. 3), the bulges 6 according to the invention are provided. These may be dimensioned differently on the inner combustion chamber wall 2 and on the outer combustion chamber wall 3. The height h and thus the penetration depth of the bulges are preferably selected so that the admixing air entering through the mixing air holes 4 is discharged in the same way as in the prior art (see FIG. 3), in which additional tubular air ducts 32 are provided.
Die Fig. 6 und 7 verdeutlichen, dass in den Wandungen der Ausbauchung 6 die Kühlluftlöcher 25 so angeordnet und positioniert sind, dass sich eine effektive Kühlung der Brennkammerwand auch im Bereich der Ausbauchungen 6 ergibt. 6 and 7 illustrate that in the walls of the bulge 6, the cooling air holes 25 are arranged and positioned so that an effective cooling of the combustion chamber wall also results in the region of the bulges 6.
Die Fig. 9 und 10 zeigen, wie auch bereits in Fig. 5 angedeutet, Möglichkeiten zur Herstellung der erfindungsgemäßen Ausbauchungen 6. Diese können von außen durch geeignete Werkzeuge 35 eingedrückt werden, welche, ähnlich einem Tiefziehwerkzeug wirken. Dabei erfolgt in den Randbereichen der äußeren und inneren Brennkammerwand 2, 3, in denen keine Ausbauchung 6 erzeugt werden soll, eine AbStützung durch geeignete Werkzeuge 35. Die von außen eindrückenden Werkzeuge können dabei eine passend ausgewählte Form aufweisen, um die Kontur der Ausbauchungen 6, welche sich beispielsweise aus Fig. 8 ergibt, zu erzeugen. In den Ausbauchungen 6 werden dann, beispielsweise durch Laserbohren oder ähnliches, die Kühlluftlöcher 25 ausgebildet, während die Mischluftlöcher 4, beispielsweise durch Laserschneiden, erzeugt werden können. Die Radien der Ausnehmungen betragen beispielsweise 10 bis 15 mm, um die Bauteilfestigkeit nicht zu beeinträchtigen und um eine Herstellung durch die Werkzeuge 35 zu ermöglichen. Diese Radien bestimmen auch den Beginn und das Ende der jeweiligen Ausbauchungen sowohl in axialer Richtung als auch in Umfangsrichtung. Wie in den Figuren dargestellt, ist die Ausbauchung 6 mit einer Anströmfläche 8 und einer Abströmfläche 9 versehen. Die Mischluftlöcher 4 können in der Anströmfläche 8 ausgebildet sein, es ist auch möglich, diese an dem Apex der jeweiligen Ausbauchung 6 vorzusehen. Die Ausbauchungen 6 sind, im Vergleich der Positionen an der inneren Brennkammerwand 2 und der äußeren Brennkammerwand 3, um den Umfang zueinander versetzt, um Zumischluft gemäß dem „counter swirl doublet mischer concept" zuzuführen, so wie dies vereinfacht in Fig. 3 gezeigt ist. FIGS. 9 and 10 show, as already indicated in FIG. 5, possibilities for producing the bulges 6 according to the invention. These can be pressed in from outside by suitable tools 35, which act similarly to a deep-drawing tool. In this case, in the edge regions of the outer and inner combustion chamber wall 2, 3, in which no bulge 6 is to be generated, a support by suitable tools 35. The impressing from the outside tools can have a suitably selected shape to the contour of the bulges 6, which results, for example, from FIG. 8. In the bulges 6, the cooling air holes 25 are then formed, for example by laser drilling or the like, while the mixing air holes 4, for example by laser cutting, can be generated. The radii of the recesses are, for example, 10 to 15 mm in order not to impair the component strength and to allow production by the tools 35. These radii also determine the beginning and the end of the respective bulges both in the axial direction and in the circumferential direction. As shown in the figures, the bulge 6 is provided with an inflow surface 8 and an outflow surface 9. The mixing air holes 4 may be formed in the inflow surface 8, it is also possible to provide these at the apex of the respective bulge 6. The bulges 6 are, compared to the positions on the inner combustion chamber wall 2 and the outer combustion chamber wall 3, circumferentially offset from each other to supply mixing air according to the "counter swirl doublet mixer concept", as shown in simplified in Fig. 3.
Wie sich aus oben stehenden Erläuterungen ergibt, können die Ausbauchungen 6 sowohl symmetrisch als auch asymmetrisch ausgebildet sein, sowohl in axialer Richtung als auch in radialer Richtung. Hierdurch ist es möglich, die Strömungsverhältnisse im Innenraum 5 der Brennkammer zu optimieren und dem„counter swirl doublet mischer concept" anzupassen. Insgesamt ergibt sich somit eine versetzte Anordnung, so wie dies beispielsweise in den Fig. 5 und 10 erläutert ist. As can be seen from the above explanations, the bulges 6 can be formed both symmetrically and asymmetrically, both in the axial direction and in the radial direction. This makes it possible to optimize the flow conditions in the interior 5 of the combustion chamber and to adapt the "counter swirl doublet mixer concept". Overall, this results in a staggered arrangement, as explained for example in FIGS. 5 and 10.
nn
Bezuaszeichenliste: Bezuaszeichenliste:
1 Triebwerksachse 1 engine axis
2 innere Brennkammerwand  2 inner combustion chamber wall
3 äußere Brennkammerwand  3 outer combustion chamber wall
4 Mischluftloch  4 mixed air hole
5 Innenraum  5 interior
6 Ausbauchung  6 bulge
7 Durchströmungsrichtung  7 flow direction
8 Anströmfläche  8 inflow area
9 Abströmfläche  9 outflow area
10 Gasturbinentriebwerk / Kerntriebwerk 10 gas turbine engine / core engine
1 1 Lufteinlass 1 1 air intake
12 Fan  12 fans
13 Mitteldruckkompressor (Verdichter) 13 medium pressure compressor (compressor)
14 Hochdruckkompressor 14 high pressure compressor
15 Brennkammer  15 combustion chamber
16 Hochdruckturbine  16 high-pressure turbine
17 Mitteldruckturbine  17 medium pressure turbine
18 Niederdruckturbine  18 low-pressure turbine
19 Abgasdüse  19 exhaust nozzle
20 Leitschaufeln  20 vanes
21 Kerntriebwerksgehäuse  21 core engine case
22 Kompressorlaufschaufeln  22 compressor blades
23 Leitschaufeln  23 vanes
24 Turbinenrotorschaufeln  24 turbine rotor blades
25 Kühlluftloch  25 cooling air hole
26 Kompressortrommel oder -scheibe 26 Compressor drum or disc
27 Turbinenrotornabe 27 turbine rotor hub
28 Auslasskonus  28 outlet cone
29 Kopfplatte  29 headstock
30 Aussparung  30 recess
31 Treibstoffdüse  31 fuel nozzle
32 Luftführung  32 air duct
33 Brennkammerkopf  33 combustion chamber head
34 Außengehäuse  34 outer casing
35 Werkzeug  35 tool

Claims

Patentansprüche claims
1 . Gasturbinenbrennkammer mit einer inneren Brennkammerwand (2) und einer äußeren Brennkammerwand (3), welche eine Ringbrennkammer bilden, wobei in der inneren Brennkammerwand (2) und der äußeren Brennkammerwand (3) um den Umfang verteilt Mischluftlöcher (5) ausgebildet sind, dadurch gekennzeichnet, dass die jeweilige1 . Gas turbine combustor having an inner combustion chamber wall (2) and an outer combustion chamber wall (3) forming an annular combustion chamber, mixing air holes (5) being distributed around the circumference in the inner combustion chamber wall (2) and the outer combustion chamber wall (3), characterized that the respective
Brennkammerwand (2, 3) im Bereich der Mischluftlöcher (4) zum Innenraum (5) der Brennkammerwand (15) ausgebaucht ist, wobei das Mischluftloch (4) in der Ausbauchung (6) angeordnet ist. Combustion chamber wall (2, 3) in the region of the mixing air holes (4) to the interior (5) of the combustion chamber wall (15) is bulged, wherein the mixing air hole (4) in the bulge (6) is arranged.
2. Gasturbinenbrennkammer nach Anspruch 1 , dadurch gekennzeichnet, dass am Umfang verteilt mehrere Ausbauchungen (6) ausgebildet sind. 2. Gas turbine combustor according to claim 1, characterized in that distributed over the circumference a plurality of bulges (6) are formed.
3. Gasturbinenbrennkammer nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Ausbauchungen (6) der inneren Brennkammerwand (2) und der äußeren Brennkammerwand (3) zueinander versetzt angeordnet sind. 3. Gas turbine combustor according to claim 1 or 2, characterized in that the bulges (6) of the inner combustion chamber wall (2) and the outer combustion chamber wall (3) are arranged offset from one another.
4. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass in einer Ausbauchung (6) eines oder mehrere Mischluftlöcher (4) angeordnet sind. 4. Gas turbine combustor according to one of claims 1 to 3, characterized in that in a bulge (6) one or more mixing air holes (4) are arranged.
5. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Ausbauchungen (6) gerundete Seitenflächen aufweisen. 5. Gas turbine combustor according to one of claims 1 to 4, characterized in that the bulges (6) have rounded side surfaces.
6. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Ausbauchungen (6), bezogen auf die Durchströmungsrichtung (7) der Brennkammer (15) eine zur jeweiligen Brennkammerwand (2, 3) in einem kleineren6. Gas turbine combustor according to one of claims 1 to 5, characterized in that the bulges (6), based on the flow direction (7) of the combustion chamber (15) to the respective combustion chamber wall (2, 3) in a smaller
Winkel ausgebildete Anströmfläche (8) und in einem hierzu größeren Winkel ausgebildete Abströmfläche (9) aufweisen. Have trained angle inflow surface (8) and in this case a larger angle formed outflow surface (9).
7. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Mischluftlöcher (4) zueinander verschiedene Durchmesser aufweisen. 7. Gas turbine combustor according to one of claims 1 to 6, characterized in that the mixing air holes (4) have mutually different diameters.
8. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass eine Höhe (h) der Ausbauchung (6) zwischen 7,5% und 25% der Höhe (H) der Brennkammer (15) beträgt. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass das Mischluftloch (4) an einer Anströmfläche (8) der Ausbauchung (6), bezogen auf die Durchströmungsrichtung (7) der Brennkammer (15), ausgebildet ist. 8. Gas turbine combustor according to one of claims 1 to 7, characterized in that a height (h) of the bulge (6) between 7.5% and 25% of the height (H) of the combustion chamber (15). Gas turbine combustor according to one of claims 1 to 8, characterized in that the mixing air hole (4) on an inflow surface (8) of the bulge (6), based on the flow direction (7) of the combustion chamber (15) is formed.
0. Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Wandung der Ausbauchung (6) mit Kühlluftlöchern (25) versehen ist. 0. gas turbine combustor according to one of claims 1 to 9, characterized in that the wall of the bulge (6) with cooling air holes (25) is provided.
EP16822139.8A 2016-02-01 2016-12-15 Gas turbine combustion chamber having a wall contour Active EP3245451B1 (en)

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Application Number Priority Date Filing Date Title
DE102016201452.8A DE102016201452A1 (en) 2016-02-01 2016-02-01 Gas turbine combustor with wall contouring
PCT/EP2016/081220 WO2017133819A1 (en) 2016-02-01 2016-12-15 Gas turbine combustion chamber having a wall contour

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EP3245451A1 true EP3245451A1 (en) 2017-11-22
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US11940151B2 (en) * 2022-01-12 2024-03-26 General Electric Company Combustor with baffle

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DE102016201452A1 (en) 2017-08-03
WO2017133819A1 (en) 2017-08-10
US20180156459A1 (en) 2018-06-07
US10670270B2 (en) 2020-06-02
EP3245451B1 (en) 2019-08-21

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