EP2918914A1 - Combustion chamber of a gas turbine - Google Patents
Combustion chamber of a gas turbine Download PDFInfo
- Publication number
- EP2918914A1 EP2918914A1 EP15158435.6A EP15158435A EP2918914A1 EP 2918914 A1 EP2918914 A1 EP 2918914A1 EP 15158435 A EP15158435 A EP 15158435A EP 2918914 A1 EP2918914 A1 EP 2918914A1
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- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- chamber wall
- wall
- shingles
- chamber according
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- 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.)
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Classifications
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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
- F23R3/002—Wall structures
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00017—Assembling combustion chamber liners or subparts
Definitions
- the invention relates to the combustion chamber of a gas turbine.
- the combustion chamber has an outer combustion chamber wall and an inner combustion chamber wall.
- the inner, hot combustion chamber wall on the outer, cold combustion chamber wall in a suitable manner.
- the two combustion chamber walls are spaced apart from one another in order to create a gap for the flow of cooling air.
- the outer, cold combustion chamber wall in this case has a plurality of impingement cooling holes, through which cooling air impinges on the side facing away from the combustion chamber interior side of the inner, hot combustion chamber wall in order to cool them.
- the inner, hot combustor wall is provided with a plurality of effusion holes through which cooling air exits which abuts the surface of the inner combustor wall to cool and shield it from the hot combustion gases.
- Such combustion chambers are arranged between a high-pressure compressor and a high-pressure turbine.
- the outer, cold combustion chamber wall which forms a support structure, is usually produced by welding prefabricated parts. At the discharge area of the combustion chamber, flanges and combustion chamber suspensions made as separate forgings are welded to support the combustion chamber.
- the combustion chamber walls themselves are usually designed as sheet metal construction.
- a combustion chamber head is provided with a base plate usually made as a casting.
- the inner, hot combustion chamber wall is then inserted.
- This usually consists of shingles, which are formed like a segment. The shingles are formed as castings and have cast-stud bolts, which are guided by recesses of the outer combustion chamber wall and screwed from the outside via nuts.
- Such constructions are for example from the US 5,435,139 A or the US 5,758,503 A previously known.
- the cooling of the shingles in the vicinity of the studs can not be optimally designed because of the material accumulations occurring there. Thus occur at the transition areas from the shingles to the stud higher temperatures that exceed the temperatures in the rest of the shingles.
- a seal or sealing lip is provided in the region of the outlet nozzle of the combustion chamber, which seals the exhaust gas jet to the surrounding components and feeds them to the guide vanes of the high-pressure turbine. These sealing lips wear out when the shingles become loose or the shingles vibrate. It proves to be disadvantageous that the sealing lip is formed as part of the support structure of the combustion chamber and can not be replaced in a simple manner.
- the invention has for its object to provide a combustion chamber of a gas turbine of the type mentioned, which has a high level of reliability and a long service life with a simple structure and simple, cost-effective manufacturability.
- the inner combustion chamber wall at its rear end, relative to the flow direction of the combustion chamber longitudinally displaceable in a groove in the region of a combustion chamber suspension or a Sealing lip for a strip seal to an outlet nozzle guide vane (NGV) is held.
- NVG outlet nozzle guide vane
- the internal second, hot combustion chamber wall can be made of a sheet material or in the form of cast segments or shingles.
- the inner combustion chamber wall shingles
- This fixation can be done according to the invention, for example by screws or bolts. According to the invention, there is thus a positive fixing at the front region of the inner combustion chamber wall.
- the inner combustion chamber wall has at least one hook or hook element at its rear end region.
- the hook is preferably U-shaped, so that the rear portion of the inner combustion chamber is both held by the hook, and is guided longitudinally displaceable.
- a plurality of hooks are provided around the circumference of the inner combustion chamber wall.
- the hooks can continue to be elastic for game clearance. They have a spring function to keep the inner combustion chamber wall (shingles) taut on the outer combustion chamber wall.
- the inner combustion chamber wall is formed segmented, wherein the segments can extend over the entire length of the combustion chamber.
- the fastening or fixing of the front end of the combustion chamber wall can be adapted in a favorable manner to the respective structural requirements, for example, by screws, which, based on the flow direction or a central axis of the combustion chamber are arranged radially.
- These stud bolts can be fastened with nuts on the cold side of the combustion head plate.
- An essential advantage of the invention results from the fact that the cooling of the inner combustion chamber wall can be optimally designed over its entire surface. Since there are no stud bolts, there are no restrictions in terms of heat transfer.
- the combustion chamber according to the invention and in particular the inner combustion chamber wall according to the invention can be produced preferably by means of an additive manufacturing process, for example by laser deposition welding or electron beam deposition welding.
- This manufacturability is promoted by the fact that, compared to the prior art, no fastening bolts or the like are required to support the inner combustion chamber wall. As a result, material accumulations and geometries, which make the production more complicated avoided.
- Another advantage of the embodiment according to the invention is that it is possible to form the sealing lip to the outlet nozzle guide ring so that it can be renewed with an exchange of the inner combustion chamber wall, without the entire combustion chamber construction is affected.
- the gas turbine engine 110 is a generalized example of a turbomachine, in which the invention can be applied.
- the engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119, which are all arranged around a central engine center axis 101.
- the intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, that radially inwardly from the engine casing 121 in an annular flow passage through the compressors 113, 114 protrude.
- the compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disc 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.
- the turbine sections 116, 117, 118 have similar stages, including an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124 projecting outwardly from a rotatable hub 126.
- the compressor drum or compressor disk 125 and the vanes 122 disposed thereon and the turbine rotor hub 126 and turbine blades 124 disposed thereon rotate about the engine centerline 101 during operation.
- the Fig. 2 shows a longitudinal sectional view of a known from the prior art combustion chamber wall in an enlarged view.
- a combustion chamber 1 with a central axis 25 is shown, which comprises a combustion chamber head 3, a base plate 8 and a heat shield 2.
- a burner seal is provided with the reference numeral 4.
- the combustion chamber 1 has an outer cold combustion chamber wall 7, to which an inner, hot combustion chamber wall 6 is attached.
- For supplying mixed air Zumischlöcher 5 are provided.
- the presentation of impingement cooling holes and effusion holes has been omitted for clarity.
- the inner combustion chamber wall 6 is provided with bolts 13, which are designed as threaded bolts and are screwed by means of nuts 14.
- a sealing lip 20 is provided for a strip seal to the outlet nozzle guide vane.
- the Fig. 3 shows a first embodiment of a combustion chamber according to the invention.
- This is basically structured as the in Fig. 2 shown combustion chamber. This means that it also has an outer cold combustion chamber wall 7 and an inner, hot combustion chamber wall 6.
- the storage is also via combustion chamber suspensions 11 and combustion chamber flanges 12. Also the Sealing lip 20 is shown accordingly.
- a combustion chamber head 3 At the front end, a combustion chamber head 3, a heat shield 2, a base plate 8 and a burner seal 4 are provided.
- the base plate 8 is provided with a groove 16, preferably an annular groove, in which the head-side end 15 of the inner, hot combustion chamber wall 6 is inserted.
- the head-side end 15 is fixed by means of fastening screws 17.
- the fixation is possible as an alternative to the screws with other positive connection elements.
- the base plate 8 threaded recesses, in which the screws 17 are screwed.
- the inner combustion chamber wall 6 is provided with radially outwardly directed hooks 18, which are guided longitudinally displaceably in recesses 19 of the outer combustion chamber wall 7.
- the mounting of the hooks 18 can take place directly on the outer combustion chamber wall 7 or in the region of a sealing lip 20 of a strip seal to an outlet nozzle guide vane (NGV).
- NVG outlet nozzle guide vane
- Fig. 4, 5 . 7 and 9 each show different design variants of the storage of the rear end portion of the inner combustion chamber wall 6.
- Die Fig. 4 clarifies in an enlarged view the in Fig. 3 shown solution. From the back view of the Fig. 6 shows that distributed on the circumference of the inner combustion chamber wall 6 a plurality of hooks 18 may be formed.
- a securing lug 21 is provided at the free end of the hook 18, which in particular facilitates the assembly of the inner combustion chamber wall 6 and prevents loosening of the hook 18.
- Fig. 7 A similar embodiment is in Fig. 7 shown.
- the recess 19 is provided with a stepped cross-section, as it turns out Fig. 8 results.
- FIGS. 9 and 10 shows a resilient projection 22 which is formed at the free end of the hook 18 and abuts against the outer combustion chamber wall 7 to bias the inner combustion chamber wall backlash.
Abstract
Die Erfindung bezieht sich auf eine Brennkammer einer Gasturbine, mit einer äußeren Brennkammerwand (7) sowie mit einer inneren Brennkammerwand (6), wobei die innere Brennkammerwand (6) an ihrem, bezogen auf die Durchströmungsrichtung der Brennkammer, vorderen Endbereich an der äußeren Brennkammerwand (7) fixiert ist und an ihrem hinteren Endbereich längsverschiebbar an der äußeren Brennkammerwand (7) gehalten ist.The invention relates to a combustion chamber of a gas turbine, with an outer combustion chamber wall (7) and with an inner combustion chamber wall (6), wherein the inner combustion chamber wall (6) at its, relative to the direction of flow of the combustion chamber, the front end region on the outer combustion chamber wall ( 7) is fixed and is held at its rear end portion longitudinally displaceable on the outer combustion chamber wall (7).
Description
Die Erfindung bezieht sich auf die Brennkammer einer Gasturbine. Die Brennkammer weist eine äußere Brennkammerwand sowie eine innere Brennkammerwand auf.The invention relates to the combustion chamber of a gas turbine. The combustion chamber has an outer combustion chamber wall and an inner combustion chamber wall.
Aus dem Stand der Technik ist es bekannt, die innere, heiße Brennkammerwand an der äußeren, kalten Brennkammerwand in geeigneter Weise zu lagern. Die beiden Brennkammerwände sind dabei voneinander beabstandet, um einen Zwischenraum zur Durchströmung von Kühlluft zu schaffen. Die äußere, kalte Brennkammerwand weist dabei eine Vielzahl von Prallkühllöchern auf, durch welche Kühlluft auf die dem Brennkammerinnenraum abgewandte Seite der inneren, heißen Brennkammerwand auftrifft, um diese zu kühlen. Die innere, heiße Brennkammerwand ist mit einer Vielzahl von Effusionslöchern versehen, durch welche Kühlluft austritt, welche sich an die Oberfläche der inneren Brennkammerwand anlegt, um diese zu kühlen und gegenüber den heißen Verbrennungsgasen abzuschirmen.From the prior art it is known to store the inner, hot combustion chamber wall on the outer, cold combustion chamber wall in a suitable manner. The two combustion chamber walls are spaced apart from one another in order to create a gap for the flow of cooling air. The outer, cold combustion chamber wall in this case has a plurality of impingement cooling holes, through which cooling air impinges on the side facing away from the combustion chamber interior side of the inner, hot combustion chamber wall in order to cool them. The inner, hot combustor wall is provided with a plurality of effusion holes through which cooling air exits which abuts the surface of the inner combustor wall to cool and shield it from the hot combustion gases.
Derartige Brennkammern sind zwischen einem Hochdruckverdichter und einer Hochdruckturbine angeordnet.Such combustion chambers are arranged between a high-pressure compressor and a high-pressure turbine.
Die äußere, kalte Brennkammerwand, welche eine Tragstruktur bildet, wird üblicherweise durch Verschweißen vorgefertigter Teile hergestellt. Am Ausströmbereich der Brennkammer werden Flansche und Brennkammeraufhängungen, welche als separate Schmiedeteile gefertigt sind, angeschweißt, um die Brennkammer zu lagern. Die Brennkammerwände selbst sind üblicherweise als Blechkonstruktion ausgeführt. Am vorderen Ende der Brennkammer ist ein Brennkammerkopf mit einer üblicherweise als Gussteil hergestellten Grundplatte vorgesehen. In dem Innenraum dieser äußeren, kalten Brennkammerwand wird dann die innere, heiße Brennkammerwand eingefügt. Diese besteht üblicherweise aus Schindeln, welche segmentartig ausgebildet sind. Die Schindeln sind als Gussteile ausgebildet und weisen angegossene Stehbolzen auf, welche durch Ausnehmungen der äußeren Brennkammerwand geführt und von außen über Muttern verschraubt werden.The outer, cold combustion chamber wall, which forms a support structure, is usually produced by welding prefabricated parts. At the discharge area of the combustion chamber, flanges and combustion chamber suspensions made as separate forgings are welded to support the combustion chamber. The combustion chamber walls themselves are usually designed as sheet metal construction. At the front end of the combustion chamber, a combustion chamber head is provided with a base plate usually made as a casting. In the interior of this outer, cold combustion chamber wall, the inner, hot combustion chamber wall is then inserted. This usually consists of shingles, which are formed like a segment. The shingles are formed as castings and have cast-stud bolts, which are guided by recesses of the outer combustion chamber wall and screwed from the outside via nuts.
Derartige Konstruktionen sind beispielsweise aus der
Bei den aus dem Stand der Technik bekannten Lösungen werden somit stets Stehbolzen verwendet, um die innere Brennkammerwand (die Schindeln) zu befestigen. Um diese Befestigung funktionsgerecht durchzuführen, ist es erforderlich, die Stehbolzen mittels der Muttern vorzuspannen. Durch die hohe Temperatur auf der Seite der heißen, inneren Brennkammerwand, wird jedoch der Werkstoff der Stehbolzen so beansprucht, dass der Werkstoff kriecht. Hierdurch baut sich die Vorspannung der Stehbolzen ab. Als Folge treten Vibrationen der Schindeln der inneren Brennkammerwand auf. Dies kann zum Versagen der Befestigung der Schindeln führen und die gesamte Gasturbine zerstören.In the solutions known from the prior art, stud bolts are thus always used to fasten the inner combustion chamber wall (the shingles). To perform this attachment functionally, it is necessary to bias the studs by means of the nuts. Due to the high temperature on the side of the hot, inner combustion chamber wall, however, the material of the stud is claimed so that the material creeps. As a result, the bias of the studs is reduced. As a result, vibrations of the shingles of the inner combustion chamber wall occur. This can lead to the failure of the attachment of the shingles and destroy the entire gas turbine.
Die Kühlung der Schindeln in der Nähe der Stehbolzen kann wegen der dort auftretenden Materialanhäufungen nicht optimal gestaltet werden. Somit treten an den Übergangsbereichen von den Schindeln zu den Stehbolzen höhere Temperaturen auf, die die Temperaturen im restlichen Bereich der Schindeln übertreffen.The cooling of the shingles in the vicinity of the studs can not be optimally designed because of the material accumulations occurring there. Thus occur at the transition areas from the shingles to the stud higher temperatures that exceed the temperatures in the rest of the shingles.
Ein weiterer Nachteil der vorbekannten Lösungen besteht darin, dass im Bereich der Austrittsdüse der Brennkammer eine Dichtung oder Dichtlippe vorgesehen ist, welche den Abgasstrahl zu den umgebenden Bauteilen hin abdichtet und diesen zu den Leitschaufeln der Hochdruckturbine zuführt. Diese Dichtlippen verschleißen bei Lockerung der Schindeln oder bei Vibrationen der Schindeln. Dabei erweist es sich als nachteilig, dass die Dichtlippe als Teil der Tragstruktur der Brennkammer ausgebildet ist und nicht in einfacher Weise ausgetauscht werden kann.Another disadvantage of the previously known solutions is that a seal or sealing lip is provided in the region of the outlet nozzle of the combustion chamber, which seals the exhaust gas jet to the surrounding components and feeds them to the guide vanes of the high-pressure turbine. These sealing lips wear out when the shingles become loose or the shingles vibrate. It proves to be disadvantageous that the sealing lip is formed as part of the support structure of the combustion chamber and can not be replaced in a simple manner.
Der Erfindung liegt die Aufgabe zugrunde, eine Brennkammer einer Gasturbine der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit ein hohes Maß an Betriebssicherheit und eine hohe Lebensdauer aufweist.The invention has for its object to provide a combustion chamber of a gas turbine of the type mentioned, which has a high level of reliability and a long service life with a simple structure and simple, cost-effective manufacturability.
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
Erfindungsgemäß ist somit vorgesehen, dass die innere Brennkammerwand an ihrem hinteren Endbereich, bezogen auf die Durchströmungsrichtung der Brennkammer, längs verschiebbar in einer Nut im Bereich einer Brennkammeraufhängung oder einer Dichtlippe für eine Streifendichtung zu einer Austrittsdüsenleitschaufel (NGV) gehalten ist. An ihrem vorderen Endbereich ist die innere Brennkammerwand an der äußeren Brennkammerwand fixiert.According to the invention it is thus provided that the inner combustion chamber wall at its rear end, relative to the flow direction of the combustion chamber, longitudinally displaceable in a groove in the region of a combustion chamber suspension or a Sealing lip for a strip seal to an outlet nozzle guide vane (NGV) is held. At its front end region, the inner combustion chamber wall is fixed to the outer combustion chamber wall.
Bei der erfindungsgemäßen Lösung ist es möglich, die erste, kalte Brennkammerwand so auszubilden, wie dies aus dem Stand der Technik bekannt ist, nämlich als gefügtes Blechteil. Die innenliegende zweite, heiße Brennkammerwand kann aus einem Blechmaterial oder in Form von gegossenen Segmenten oder Schindeln hergestellt werden. Durch die Lagerung in einer Nut am hinteren Endbereich der kalten Brennkammerwand ist es möglich, eine Längsverschiebbarkeit zu ermöglichen, welche insbesondere auch thermische Ausdehnungen zulässt, ohne dass die Gefahr von Beschädigungen besteht. Am vorderen Ende ist die innere Brennkammerwand (Schindel) in der Nähe der Grundplatte fixiert. Diese Fixierung kann erfindungsgemäß beispielsweise durch Schrauben oder Bolzen erfolgen. Erfindungsgemäß liegt somit am vorderen Bereich der inneren Brennkammerwand eine formschlüssige Fixierung vor.In the solution according to the invention, it is possible to form the first, cold combustion chamber wall, as is known from the prior art, namely as a joined sheet metal part. The internal second, hot combustion chamber wall can be made of a sheet material or in the form of cast segments or shingles. By mounting in a groove at the rear end of the cold combustion chamber wall, it is possible to allow a longitudinal displacement, which in particular also allows thermal expansion, without the risk of damage. At the front end, the inner combustion chamber wall (shingles) is fixed near the base plate. This fixation can be done according to the invention, for example by screws or bolts. According to the invention, there is thus a positive fixing at the front region of the inner combustion chamber wall.
In besonders günstiger Ausgestaltung der Erfindung ist vorgesehen, dass die innere Brennkammerwand an ihrem hinteren Endbereich zumindest einen Haken oder ein Hakenelement aufweist. Der Haken ist bevorzugterweise U-förmig ausgebildet, so dass der hintere Bereich der inneren Brennkammer mittels des Hakens sowohl gehalten wird, als auch längsverschiebbar geführt ist. Bevorzugterweise sind um den Umfang der inneren Brennkammerwand mehrere Haken vorgesehen. Die Haken können weiterhin zur Spielbeseitigung elastisch ausgebildet sein. Dabei weisen sie eine Federfunktion auf, um die innere Brennkammerwand (Schindeln) straff an der äußeren Brennkammerwand zu halten. Durch die nach außen, vom heißen inneren Bereich der inneren Brennkammerwand abgewandte Ausgestaltung des Hakens befindet sich dieser außerhalb des Heißgasstroms und wird somit thermisch nicht so stark belastet.In a particularly favorable embodiment of the invention, it is provided that the inner combustion chamber wall has at least one hook or hook element at its rear end region. The hook is preferably U-shaped, so that the rear portion of the inner combustion chamber is both held by the hook, and is guided longitudinally displaceable. Preferably, a plurality of hooks are provided around the circumference of the inner combustion chamber wall. The hooks can continue to be elastic for game clearance. They have a spring function to keep the inner combustion chamber wall (shingles) taut on the outer combustion chamber wall. By facing away from the hot inner region of the inner combustion chamber wall configuration of the hook, this is outside of the hot gas stream and is thus not thermally stressed so much.
In günstiger Weiterbildung der Erfindung kann vorgesehen sein, dass die innere Brennkammerwand segmentiert ausgebildet ist, wobei sich die Segmente über die gesamte Länge der Brennkammer erstrecken können.In a favorable development of the invention it can be provided that the inner combustion chamber wall is formed segmented, wherein the segments can extend over the entire length of the combustion chamber.
Die Befestigung oder Fixierung des vorderen Endes der Brennkammerwand kann in günstiger Weise den jeweiligen baulichen Anforderungen angepasst werden, beispielsweise durch Schrauben, welche, bezogen auf die Durchströmungsrichtung oder eine Mittelsachse der Brennkammer radial angeordnet sind. Alternativ kann die Befestigung durch axial eingerichtete Stehbolzen, die mit den Schindeln hergestellt sind, erfolgen. Diese Stehbolzen können mit Muttern auf der kalten Seite der Brennkammerkopfplatte befestigt werden.The fastening or fixing of the front end of the combustion chamber wall can be adapted in a favorable manner to the respective structural requirements, for example, by screws, which, based on the flow direction or a central axis of the combustion chamber are arranged radially. Alternatively, the attachment by axially aligned studs, which are made with the shingles, take place. These stud bolts can be fastened with nuts on the cold side of the combustion head plate.
Als wesentlicher Vorteil ergibt sich erfindungsgemäß, dass die Kühlung der inneren Brennkammerwand auf ihrer gesamten Fläche optimal gestaltet werden kann. Da keine Stehbolzen vorhanden sind, ergeben sich auch keine Einschränkungen hinsichtlich der Wärmeübertragung.An essential advantage of the invention results from the fact that the cooling of the inner combustion chamber wall can be optimally designed over its entire surface. Since there are no stud bolts, there are no restrictions in terms of heat transfer.
Die erfindungsgemäße Brennkammer und insbesondere die erfindungsgemäße innere Brennkammerwand kann bevorzugterweise mittels eines additiven Fertigungsverfahrens hergestellt werden, beispielsweise durch Laserauftragsschweißen oder Elektronenstrahlauftragsschweißen. Diese Herstellbarkeit wird dadurch gefördert, dass, im Vergleich zum Stand der Technik, keine Befestigungsbolzen oder ähnliches erforderlich sind, um die innere Brennkammerwand zu lagern. Hierdurch werden Materialanhäufungen sowie Geometrien, welche die Herstellung komplizierter machen, vermieden.The combustion chamber according to the invention and in particular the inner combustion chamber wall according to the invention can be produced preferably by means of an additive manufacturing process, for example by laser deposition welding or electron beam deposition welding. This manufacturability is promoted by the fact that, compared to the prior art, no fastening bolts or the like are required to support the inner combustion chamber wall. As a result, material accumulations and geometries, which make the production more complicated avoided.
Ein weiterer Vorteil der erfindungsgemäßen Ausgestaltung liegt darin, dass es möglich ist, die Dichtlippe zum Austrittsdüsenleitschaufelring so auszubilden, dass diese bei einem Austausch der inneren Brennkammerwand mit erneuert werden kann, ohne dass die gesamte Brennkammerkonstruktion betroffen ist.Another advantage of the embodiment according to the invention is that it is possible to form the sealing lip to the outlet nozzle guide ring so that it can be renewed with an exchange of the inner combustion chamber wall, without the entire combustion chamber construction is affected.
Im Folgenden wird die Erfindung anhand von Ausführungsbeispielen in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:
- Fig. 1
- eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung;
- Fig. 2
- eine Längs-Schnittansicht einer Brennkammer gemäß dem Stand der Technik;
- Fig. 3
- eine Ansicht, analog
Fig. 2 , eines ersten Ausführungsbeispiels der Erfindung; - Fig. 4
- eine vereinfachte Detailansicht des hinteren Endbereichs der inneren Brennkammerwand sowie deren Lagerung;
- Fig. 5
- ein abgewandeltes Ausführungsbeispiel, analog
Fig. 4 ; - Fig. 6
- eine stirnseitige Rückansicht des Ausführungsbeispiels der
Fig. 4 ; - Fig. 7 und 8
- ein weiteres Ausführungsbeispiel mit Rückansicht in analoger Darstellung zu den
Fig. 4 ; undund 6 - Fig. 9 und 10
- eine weitere Ausgestaltungsvariante, analog den
Fig. 7 .und 8
- Fig. 1
- a schematic representation of a gas turbine engine according to the present invention;
- Fig. 2
- a longitudinal sectional view of a combustion chamber according to the prior art;
- Fig. 3
- a view, analog
Fig. 2 a first embodiment of the invention; - Fig. 4
- a simplified detail of the rear end portion of the inner combustion chamber wall and its storage;
- Fig. 5
- a modified embodiment, analog
Fig. 4 ; - Fig. 6
- a front-side rear view of the embodiment of the
Fig. 4 ; - FIGS. 7 and 8
- a further embodiment with rear view in an analogous representation to the
4 and 6 ; and - FIGS. 9 and 10
- a further embodiment variant, analogous to
FIGS. 7 and 8 ,
Das Gasturbinentriebwerk 110 gemäß
Der Mitteldruckkompressor 113 und der Hochdruckkompressor 114 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 120 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Triebwerksgehäuse 121 in einem ringförmigen Strömungskanal durch die Kompressoren 113, 114 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 122 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 125 vorstehen, die mit Naben 126 der Hochdruckturbine 116 bzw. der Mitteldruckturbine 117 gekoppelt sind.The
Die Turbinenabschnitte 116, 117, 118 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 123, die radial nach innen vom Gehäuse 121 in den ringförmigen Strömungskanal durch die Turbinen 116, 117, 118 vorstehen, und eine nachfolgende Anordnung von Turbinenschaufeln 124, die nach außen von einer drehbaren Nabe 126 vorstehen. Die Kompressortrommel oder Kompressorscheibe 125 und die darauf angeordneten Schaufeln 122 sowie die Turbinenrotornabe 126 und die darauf angeordneten Turbinenlaufschaufeln 124 drehen sich im Betrieb um die Triebwerksmittelachse 101.The
Die
Die innere Brennkammerwand 6 ist mit Bolzen 13 versehen, welche als Gewindebolzen ausgeführt sind und mittels Muttern 14 verschraubt sind. Am ausströmseitigen Ende der Brennkammer 1 ist eine Dichtlippe 20 für eine Streifendichtung zur Austrittsdüsenleitschaufel vorgesehen. Die Lagerung der Brennkammer 1 erfolgt über Brennkammerflansche 12 und Brennkammeraufhängungen 11.The inner
In den folgenden Ausführungsbeispielen sind gleiche Teile mit gleichen Bezugsziffern versehen. Gleiche Teile und gleiche Lösungsaspekte sind bei den unterschiedlichen Ausführungsbeispielen nicht jeweils nochmals detailliert beschrieben, es wird diesbezüglich auf den Text der anderen Ausführungsbeispiele verwiesen.In the following embodiments, like parts are given the same reference numerals. The same parts and the same solution aspects are not described again in detail in the different embodiments, reference is made in this regard to the text of the other embodiments.
Die
Wie in
Am hinteren Endbereich ist die innere Brennkammerwand 6 mit radial nach außen gerichteten Haken 18 versehen, welche in Ausnehmungen 19 der äußeren Brennkammerwand 7 längsverschiebbar geführt sind. Die Lagerung der Haken 18 kann direkt an der äußeren Brennkammerwand 7 oder im Bereich einer Dichtlippe 20 einer Streifendichtung zu einer Austrittsdüsenleitschaufel (NGV) erfolgen.At the rear end region, the inner
Die
Bei dem Ausführungsbeispiel der
- 11
- Brennkammercombustion chamber
- 22
- Hitzeschildheat shield
- 33
- Brennkammerkopfbulkhead
- 44
- BrennerdichtungBrenner seal
- 55
- ZumischlochZumischloch
- 66
- innere, heiße Brennkammerwand/Segment/Schindelinner, hot combustion chamber wall / segment / shingles
- 77
- äußere, kalte Brennkammerwandouter, cold combustion chamber wall
- 88th
- Grundplattebaseplate
- 99
- PrallkühllochImpingement cooling hole
- 1010
- Effusionslocheffusion
- 1111
- Brennkammeraufhängungcombustion chamber suspension
- 1212
- BrennkammerflanschBrennkammerflansch
- 1313
- Bolzenbolt
- 1414
- Muttermother
- 1515
- kopfseitiges Ende der inneren, heißen Brennkammerwand 6Head end of the inner, hot combustion chamber wall. 6
- 1616
-
Nut in Grundplatte 8Groove in
base plate 8 - 1717
- Befestigungsschraubefixing screw
- 1818
- Hakenhook
- 1919
- Ausnehmungrecess
- 2020
- Dichtlippesealing lip
- 2121
- Sicherungsansatzassurance approach
- 2222
- elastischer Ansatzelastic approach
- 101101
- TriebwerksmittelachseEngine centerline axis
- 110110
- Gasturbinentriebwerk / KerntriebwerkGas turbine engine / core engine
- 111111
- Lufteinlassair intake
- 112112
- Fanfan
- 113113
- Mitteldruckkompressor (Verdichter)Medium pressure compressor (compressor)
- 114114
- HochdruckkompressorHigh pressure compressor
- 115115
- Brennkammercombustion chamber
- 116116
- HochdruckturbineHigh-pressure turbine
- 117117
- MitteldruckturbineIntermediate pressure turbine
- 118118
- NiederdruckturbineLow-pressure turbine
- 119119
- Abgasdüseexhaust nozzle
- 120120
- Leitschaufelnvanes
- 121121
- TriebwerksgehäuseEngine casing
- 122122
- KompressorlaufschaufelnCompressor blades
- 123123
- Leitschaufelnvanes
- 124124
- Turbinenschaufelnturbine blades
- 125125
- Kompressortrommel oder -scheibeCompressor drum or disc
- 126126
- TurbinenrotornabeTurbinenrotornabe
- 127127
- Auslasskonusoutlet cone
Claims (10)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102014204476.6A DE102014204476A1 (en) | 2014-03-11 | 2014-03-11 | Combustion chamber of a gas turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2918914A1 true EP2918914A1 (en) | 2015-09-16 |
Family
ID=52633151
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15158435.6A Withdrawn EP2918914A1 (en) | 2014-03-11 | 2015-03-10 | Combustion chamber of a gas turbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US9335048B2 (en) |
EP (1) | EP2918914A1 (en) |
DE (1) | DE102014204476A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3392567A1 (en) * | 2017-04-18 | 2018-10-24 | United Technologies Corporation | Combustor liner panel end rail |
FR3097028A1 (en) * | 2019-06-07 | 2020-12-11 | Safran Helicopter Engines | A method of manufacturing a flame tube for a turbomachine |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
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US10830433B2 (en) | 2016-11-10 | 2020-11-10 | Raytheon Technologies Corporation | Axial non-linear interface for combustor liner panels in a gas turbine combustor |
US10655853B2 (en) | 2016-11-10 | 2020-05-19 | United Technologies Corporation | Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor |
US10935236B2 (en) | 2016-11-10 | 2021-03-02 | Raytheon Technologies Corporation | Non-planar combustor liner panel for a gas turbine engine combustor |
US10935235B2 (en) | 2016-11-10 | 2021-03-02 | Raytheon Technologies Corporation | Non-planar combustor liner panel for a gas turbine engine combustor |
US20180306113A1 (en) * | 2017-04-19 | 2018-10-25 | United Technologies Corporation | Combustor liner panel end rail matching heat transfer features |
US10941944B2 (en) | 2018-10-04 | 2021-03-09 | Raytheon Technologies Corporation | Consumable support structures for additively manufactured combustor components |
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US5435139A (en) | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
US5758503A (en) | 1995-05-03 | 1998-06-02 | United Technologies Corporation | Gas turbine combustor |
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EP1777460A1 (en) * | 2005-10-18 | 2007-04-25 | Snecma | Fastening of a combustion chamber inside its housing |
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2014
- 2014-03-11 DE DE102014204476.6A patent/DE102014204476A1/en not_active Withdrawn
-
2015
- 2015-03-10 US US14/643,381 patent/US9335048B2/en active Active
- 2015-03-10 EP EP15158435.6A patent/EP2918914A1/en not_active Withdrawn
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US5435139A (en) | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
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EP3392567A1 (en) * | 2017-04-18 | 2018-10-24 | United Technologies Corporation | Combustor liner panel end rail |
FR3097028A1 (en) * | 2019-06-07 | 2020-12-11 | Safran Helicopter Engines | A method of manufacturing a flame tube for a turbomachine |
Also Published As
Publication number | Publication date |
---|---|
US20150260402A1 (en) | 2015-09-17 |
DE102014204476A1 (en) | 2015-10-01 |
US9335048B2 (en) | 2016-05-10 |
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