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EP3245451B1 - Gas turbine combustion chamber having a wall contour - Google Patents

Gas turbine combustion chamber having a wall contour Download PDF

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Publication number
EP3245451B1
EP3245451B1 EP16822139.8A EP16822139A EP3245451B1 EP 3245451 B1 EP3245451 B1 EP 3245451B1 EP 16822139 A EP16822139 A EP 16822139A EP 3245451 B1 EP3245451 B1 EP 3245451B1
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EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
chamber wall
bulges
mixing
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EP16822139.8A
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German (de)
French (fr)
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EP3245451A1 (en
Inventor
Carsten DR. CLEMEN
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Publication of EP3245451A1 publication Critical patent/EP3245451A1/en
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    • 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 combustor 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.
  • gas turbine combustors are for example from the US 3,593,518 A , the EP 2 357 412 A2 and the FR 1 130 169 A known, the US 3,593,518 A discloses a gas turbine combustor according to the preamble of claim 1.
  • the invention relates to a gas turbine combustor, such as that in the WO 2014/149081 A1 is described.
  • a combustion chamber works according to the "counter swirl doublet mixer concept".
  • the combustion chamber which may be constructed in modular construction with individual, arranged around the circumference, interconnected modules, comprises an outer and an inner combustion chamber wall and a head plate, are provided in the recesses through which fuel nozzles can reach the combustion chamber.
  • the combustion chamber itself is formed so as to be single-walled, so that the outer combustion-chamber wall and the inner combustion-chamber wall are produced, for example, from formed sheet metal. Distributed around the circumference mixing air holes are provided, through which mixing air is supplied.
  • the invention has for its object to provide a gas turbine combustor of the type mentioned, which with a simple structure and easier, cheaper Manufacturability avoids the disadvantages of the prior art and allows for effective delivery of admixed air.
  • 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 to the interior of the combustion chamber is bulged, 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 according to the "counter swirl doublet mixer concept" provided pairwise mixed air holes.
  • the mixed air holes not provided by the mixed air holes, as provided in the prior art, tubular air ducts in the interior of the combustion chamber. Rather, the combustion chamber wall is bulged even locally to the interior. Since the one or more mixing holes are provided in the respective bulge, the admixing air discharged through the mixing air hole is reliably guided into the inner portion of the inner space 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 around the inner circumference of the annular combustion chamber distributed in the region of the mixing air holes arranged at 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 refers in each case to be considered sectional view of the flow direction of the combustion chamber or on the central axis thereof. Since it is an annular combustion chamber, the central axes to be considered for the individual burners are arranged on a truncated cone, as shown by the prior art. The respective central axes are thus only in one 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 mixed 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 respective mixing air hole is further provided on an inflow surface of the bulge. This also optimizes the flow guidance in connection with an improved introduction of admixed air.
  • 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, 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.
  • the gas turbine engine 10 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 10 is formed in a conventional manner and comprises in the flow direction in succession an air inlet 11, 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 a Exhaust nozzle 19, which are all arranged around 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.
  • FIGS. 2 and 3 show each combustion chamber constructions according to the "counter swirl doublet mixer concept" according to the prior art.
  • the Fig. 2 shows an axial sectional view in a simplified representation.
  • an annular combustion chamber is shown, which has an inner combustion chamber wall 2 and an outer combustion chamber wall 1 and is provided with a top plate 29 in which distributed around the circumference (s. Fig. 3 ) Recesses 30 are formed. These serve to receive fuel nozzles 31, as is known from the prior art.
  • FIGS. 2 and 3 in axial section plane or radial section plane ( Fig. 3 ) a plurality of distributed around the circumference arranged mixing air holes 4, 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 in particular in Fig. 2 is shown.
  • 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 Fig. 4 shows a sectional view analog Fig. 2 ,
  • the 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 results from Fig. 4 and forms 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 in Fig. 4 also indicated. It is between 7.5% and 25% of the total height H.
  • the Fig. 5 shows a view C according to Fig. 6 and thus a view from the downstream 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 ,
  • the Fig. 5 shows in simplified representation tools 35, which in conjunction with the FIGS. 9 and 10 be explained in more detail. These tools 35 serve to produce the bulges 6.
  • the Fig. 5 shows two radially arranged cutting lines A and B. Sectional views along these section lines A and B are in the Fig. 6 and 7 shown.
  • the Fig. 6 shows a view along section line A and illustrates the shape and arrangement of the bulges 6. These point in the flow direction 7 (s. Fig. 4 ) an inflow surface 8 and an outflow surface 9. It can be seen that the inflow surface 8 is arranged at a shallower angle to the respective combustion chamber wall 2, 3, as the outflow surface 9. This is also again in the view of Fig. 8 clarified. 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.
  • a synopsis of Fig. 5 to 7 shows that alternately in the region of the mixed air holes, which are located in a central region of the cross section of the annular combustion chamber the inner combustion chamber wall 2 and the outer combustion chamber wall 3, to match the alternating arrangement of the mixed air holes (s. 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. Fig. 3 ), in which additional tubular air ducts 32 are provided.
  • FIGS. 9 and 10 show, as already in Fig. 5 indicated, possibilities for producing the bulges 6 according to the invention.
  • These can be pressed from the outside by suitable tools 35, which act similar to a thermoforming tool.
  • suitable tools 35 which act similar to a thermoforming tool.
  • the impressing from the outside tools can have a suitably selected shape to the contour of the bulges 6, which, for example, out Fig. 8 results in generating.
  • 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 of 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 simplified in Fig. 3 is shown.
  • 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".

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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)

Description

Die Erfindung bezieht sich auf eine Gasturbinenbrennkammer gemäß den Merkmalen des Oberbegriffs des Anspruchs 1.The invention relates to a gas turbine combustor 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. Solche Gasturbinenbrennkammern sind beispielsweise aus der US 3,593,518 A , der EP 2 357 412 A2 und der FR 1 130 169 A bekannt, wobei die US 3,593,518 A eine Gasturbinenbrennkammer gemäß dem Oberbegriff des Anspruchs 1 offenbart.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. Such gas turbine combustors are for example from the US 3,593,518 A , the EP 2 357 412 A2 and the FR 1 130 169 A known, the US 3,593,518 A discloses a gas turbine combustor according to the preamble of claim 1.

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, such as that in the WO 2014/149081 A1 is described. Such a combustion chamber works according to the "counter swirl doublet mixer concept". The combustion chamber, which may be constructed in modular construction with individual, arranged around the circumference, interconnected modules, comprises an outer and an inner combustion chamber wall and a head plate, are provided in the recesses through which fuel nozzles can reach the combustion chamber. The combustion chamber itself is formed so as to be single-walled, so that the outer combustion-chamber wall and the inner combustion-chamber wall are produced, for example, from formed sheet metal. Distributed around the circumference mixing air holes are provided, through which mixing air is supplied. In each case two mixed air holes are in pairs directly 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 a burn, however, the temperature distribution at the combustion chamber outlet changes 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, which with a simple structure and easier, cheaper Manufacturability avoids the disadvantages of the prior art and allows for effective delivery of admixed air.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.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.

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 Brennkammer ausgebaucht ist, wobei das Mischluftloch in der jeweiligen Ausbauchung angeordnet ist.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 to the interior of the combustion chamber is bulged, 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 according to the "counter swirl doublet mixer concept" provided pairwise mixed air holes. Thus, not provided by the mixed air holes, as provided in the prior art, tubular air ducts in the interior of the combustion chamber. Rather, the combustion chamber wall is bulged even locally to the interior. Since the one or more mixing holes are provided in the respective bulge, the admixing air discharged through the mixing air hole is reliably guided into the inner portion of the inner space 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 Umfangangeordneten Mischluftlöcher eine wellenartige Konturierung der Brennkammerwand. Diese Konturierung ist sowohl an der inneren Brennkammerwand als auch an der äußeren Brennkammerwand vorgesehen.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 around the inner circumference of the annular combustion chamber distributed in the region of the mixing air holes arranged at the circumference. This contouring is provided both on the inner combustion chamber wall and on the outer combustion chamber wall.

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, 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" refers in each case to be considered sectional view of the flow direction of the combustion chamber or on the central axis thereof. Since it is an annular combustion chamber, the central axes to be considered for the individual burners are arranged on a truncated cone, as shown by the prior art. The respective central axes are thus only in one 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. By contrast, according to the counter swirl doublet mixer concept, the mixed 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.

Erfindungsgemäß ist ferner das jeweilige Mischluftloch an einer Anströmfläche der Ausbauchung vorgesehen. Auch hierdurch wird die Strömungsführung in Zusammenhang mit einer verbesserten Einleitung von Zumischluft optimiert.According to the invention, the respective mixing air hole is further provided on an inflow surface of the bulge. 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.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.

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.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.

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung,
Fig. 2
eine vereinfachte Axialschnittansicht einer Brennkammer gemäß dem Stand der Technik,
Fig. 3
eine Ansicht, analog Fig. 2, in einer Radialschnittebene gemäß dem Stand der Technik,
Fig. 4
eine vereinfachte Schnittansicht eines erfindungsgemäßen Ausführungsbeispiels, analog Fig. 2,
Fig. 5
eine Radialschnittansicht des Ausführungsbeispiels gemäß Fig. 4 in Darstellung, analog Fig. 3,
Fig. 6
eine Axialschnittansicht gemäß Schnittlinie A von Fig. 5,
Fig. 7
eine Ansicht, analog Fig. 6, gemäß Schnittlinie B von Fig. 5,
Fig. 8
eine schematische Innenansicht eines Teilbereichs der Brennkammerwand,
Fig. 9
eine Schnittansicht, analog Fig. 4, mit Darstellung einer Fertigungsmöglichkeit, und
Fig. 10
eine Schnittansicht, analog Fig. 5.
In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:
Fig. 1
a schematic representation of a gas turbine engine according to the present invention,
Fig. 2
a simplified axial sectional view of a combustion chamber according to the prior art,
Fig. 3
a view, analog Fig. 2 in a radial section plane according to the prior art,
Fig. 4
a simplified sectional view of an embodiment of the invention, analog Fig. 2 .
Fig. 5
a radial sectional view of the embodiment according to Fig. 4 in representation, analog Fig. 3 .
Fig. 6
an axial sectional view along section line A of Fig. 5 .
Fig. 7
a view, analog Fig. 6 , according to section line B of Fig. 5 .
Fig. 8
a schematic interior view of a portion of the combustion chamber wall,
Fig. 9
a sectional view, analog Fig. 4 , with representation of a production possibility, and
Fig. 10
a sectional view, analog 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 11, 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.The gas turbine engine 10 according to Fig. 1 is a generalized example of a turbomachine, in which the invention can be applied. The engine 10 is formed in a conventional manner and comprises in the flow direction in succession an air inlet 11, 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 a Exhaust nozzle 19, which are all arranged around a central engine axis 1.

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 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.The FIGS. 2 and 3 show each combustion chamber constructions according to the "counter swirl doublet mixer concept" according to the prior art. The Fig. 2 shows an axial sectional view in a simplified representation. In this case, an annular combustion chamber is shown, which has an inner combustion chamber wall 2 and an outer combustion chamber wall 1 and is provided with a top plate 29 in which distributed around the circumference (s. Fig. 3 ) Recesses 30 are formed. These 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, the show FIGS. 2 and 3 in axial section plane or radial section plane ( Fig. 3 ) a plurality of distributed around the circumference arranged mixing air holes 4, 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 in particular in Fig. 2 is shown.

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.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.

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.As is clear from the FIGS. 2 and 3 results, 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.In the Fig. 4 to 10 an embodiment of the invention is explained. Here are the same parts as in the FIGS. 2 and 3 provided with the same reference numerals, so that can be dispensed with a repeated description.

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.The Fig. 4 shows a sectional view analog Fig. 2 , The 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.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 results from Fig. 4 and forms 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 in Fig. 4 also indicated. It is between 7.5% and 25% of the total height 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.The Fig. 5 shows a view C according to Fig. 6 and thus a view from the downstream 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.The Fig. 5 shows in simplified representation tools 35, which in conjunction with the FIGS. 9 and 10 be explained in more detail. These tools 35 serve to produce the bulges 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".The Fig. 5 shows two radially arranged cutting lines A and B. Sectional views along these section lines A and B are in the Fig. 6 and 7 shown. The Fig. 6 shows a view along section line A and illustrates the shape and arrangement of the bulges 6. These point in the flow direction 7 (s. Fig. 4 ) an inflow surface 8 and an outflow surface 9. It can be seen that the inflow surface 8 is arranged at a shallower angle to the respective combustion chamber wall 2, 3, as the outflow surface 9. This is also again in the view of Fig. 8 clarified. 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 in the Fig. 6 and 7 shown, 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 synopsis of Fig. 5 to 7 shows that alternately in the region of the mixed air holes, which are located in a central region of the cross section of the annular combustion chamber the inner combustion chamber wall 2 and the outer combustion chamber wall 3, to match the alternating arrangement of the mixed air holes (s. 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. 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.The Fig. 6 and 7 make clear 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 area 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.The FIGS. 9 and 10 show, as already in Fig. 5 indicated, possibilities for producing the bulges 6 according to the invention. These can be pressed from the outside by suitable tools 35, which act similar to a thermoforming 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, for example, out Fig. 8 results in generating. 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 of 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 simplified in Fig. 3 is shown.

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.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".

Insgesamt ergibt sich somit eine versetzte Anordnung, so wie dies beispielsweise in den Fig. 5 und 10 erläutert ist.Overall, this results in a staggered arrangement, as for example in the Fig. 5 and 10 is explained.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
TriebwerksachseEngine axis
22
innere Brennkammerwandinner combustion chamber wall
33
äußere Brennkammerwandouter combustion chamber wall
44
MischluftlochMixed air hole
55
Innenrauminner space
66
Ausbauchungbulge
77
DurchströmungsrichtungFlow direction
88th
Anströmflächeinflow area
99
Abströmflächeoutflow
1010
Gasturbinentriebwerk / KerntriebwerkGas turbine engine / core engine
1111
Lufteinlassair intake
1212
Fanfan
1313
Mitteldruckkompressor (Verdichter)Medium pressure compressor (compressor)
1414
HochdruckkompressorHigh pressure compressor
1515
Brennkammercombustion chamber
1616
HochdruckturbineHigh-pressure turbine
1717
MitteldruckturbineIntermediate pressure turbine
1818
NiederdruckturbineLow-pressure turbine
1919
Abgasdüseexhaust nozzle
2020
Leitschaufelnvanes
2121
KerntriebwerksgehäuseCore engine casing
2222
KompressorlaufschaufelnCompressor blades
2323
Leitschaufelnvanes
2424
TurbinenrotorschaufelnTurbine rotor blades
2525
KühlluftlochCooling air hole
2626
Kompressortrommel oder -scheibeCompressor drum or disc
2727
TurbinenrotornabeTurbinenrotornabe
2828
Auslasskonusoutlet cone
2929
Kopfplatteheadstock
3030
Aussparungrecess
3131
Treibstoffdüsefuel nozzle
3232
Luftführungair duct
3333
Brennkammerkopfbulkhead
3434
Außengehäuseouter casing
3535
WerkzeugTool

Claims (9)

  1. Gas turbine combustion chamber having an inner combustion chamber wall (2) and having an outer combustion chamber wall (3), which form a ringshaped combustion chamber, wherein mixing-air holes (4) are formed in a manner distributed around the circumference in the inner combustion chamber wall (2) and the outer combustion chamber wall (3), wherein the respective combustion chamber wall (2, 3) is bulged towards the interior (5) of the combustion chamber (15) in the region of a respective mixing-air hole (4) and the respective mixing-air hole (4) is arranged in the bulge (6),
    characterized in that
    the respective mixing-air hole (4) arranged in the bulge (6) is in each case formed on a flow-on surface (8) of the bulge (6) with respect to the throughflow direction (7) of the combustion chamber (15).
  2. Gas turbine combustion chamber according to Claim 1, characterized in that multiple bulges (6) are formed in a manner distributed over the circumference.
  3. Gas turbine combustion chamber according to Claim 1 or 2, characterized in that the bulges (6) of the inner combustion chamber wall (2) and of the outer combustion wall (3) are arranged in a manner offset from one another.
  4. Gas turbine combustion chamber according to one of Claims 1 to 3, characterized in that a mixing-air hole (4) or multiple mixing-air holes (4) is/are arranged in a bulge (6).
  5. Gas turbine combustion chamber according to one of Claims 1 to 4, characterized in that the bulges (6) have rounded side surfaces.
  6. Gas turbine combustion chamber according to one of Claims 1 to 5, characterized in that the bulges (6), with respect to the throughflow direction (7) of the combustion chamber (15), have a flow-on surface (8)which is formed at a relatively small angle to the respective combustion chamber wall (2, 3) and a flow-off surface (9) which is formed at a relatively large angle thereto.
  7. Gas turbine combustion chamber according to one of Claims 1 to 6, characterized in that the mixing-air holes (4) have diameters which differ from one another.
  8. Gas turbine combustion chamber according to one of Claims 1 to 7, characterized in that a height (h) of the bulge (6) amounts to between 7.5% and 25% of the height (H) of the combustion chamber (15).
  9. Gas turbine combustion chamber according to one of Claims 1 to 8, characterized in that the wall of the bulge (6) is provided with cooling-air holes (25).
EP16822139.8A 2016-02-01 2016-12-15 Gas turbine combustion chamber having a wall contour Active EP3245451B1 (en)

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

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