EP2738470A1 - Shingle attachment assembly of a gas turbine combustion chamber - Google Patents

Shingle attachment assembly of a gas turbine combustion chamber Download PDF

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Publication number
EP2738470A1
EP2738470A1 EP13191950.8A EP13191950A EP2738470A1 EP 2738470 A1 EP2738470 A1 EP 2738470A1 EP 13191950 A EP13191950 A EP 13191950A EP 2738470 A1 EP2738470 A1 EP 2738470A1
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EP
European Patent Office
Prior art keywords
combustion chamber
shingle
chamber wall
annular flange
fastening element
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13191950.8A
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German (de)
French (fr)
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EP2738470B1 (en
Inventor
Stefan Penz
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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 EP2738470A1 publication Critical patent/EP2738470A1/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
    • F23R3/002—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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a shingle fastening arrangement of a gas turbine combustor according to the features of the preamble of claim 1.
  • the invention relates to a combustion chamber of a gas turbine, wherein on a combustion chamber wall shingles are attached, which have a distance from the combustion chamber wall.
  • the invention has for its object to provide a Schindelbefest onlysan Aunt a gas turbine combustor, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and good cooling, especially the shingles allows.
  • the shingle is provided with an annular flange arranged on its side facing the combustion chamber wall.
  • This annular flange is dimensioned to fit a recess of the combustion chamber wall and engages either in this recess or is flush with the edge of the recess on the combustion chamber wall.
  • the fastener extends through the recess of the combustion chamber wall and is mechanically connected to the annular flange. This connection with the annular flange can be done either directly.
  • the annular flange on its inside a thread, which is in engagement with a threaded extension of the fastener.
  • a mixed-air tube which is provided with an internal thread and is screwed to the fastening element.
  • the annular flange is clamped between the Mischluftleitrohr and the fastener, so that the shingle is firmly clamped against the combustion chamber wall.
  • the fastening element is round. It may, unless a Mischluftleitrohr is used, be designed cup-like. That's it particularly favorable if in the central region of the cup-like configuration of the fastening element air passage recesses are provided, through which cooling air can be fed to the shingle.
  • the shingle is also preferably provided adjacent to the central region of the fastener with air passage recesses to pass cooling air to the hot side of the shingle.
  • the embodiment according to the invention it is thus possible to realize an efficient impact-effusion cooling between the shingle and the combustion chamber wall (shingle support). As a result, high temperatures in the region of attachment of the shingle to the combustion chamber wall are avoided.
  • the inventively provided annular flange can be dimensioned so that it requires only a very small area of the shingle, so that there is no disturbance of the cooling air film on the hot side of the shingle during operation.
  • the annular flange can have a very small height. Due to the smaller height of the annular flange compared to a threaded pin, the introduction of effusion cooling air recesses by means of e.g. Laser or electron beam less obstructed. This makes it possible to bring effusion cooling air recesses closer to the joint, i.e. to the annular flange. As a result, the cooling film on the hot side of the shingle is not or only slightly disturbed.
  • the shingle attachment arrangement according to the invention is characterized by a number of significant advantages. On the one hand, it is possible to realize a lower overall height. As a result, it is possible in the sequence to allow smaller combustion chamber or larger combustion chamber volume with the same space. This leads to a lower weight of the combustion chamber and to a saving in material and manufacturing costs. Furthermore, it is possible according to the invention to effectively cool the area of the shingle attachment. As a result, hot areas, as they occur in the prior art, avoided. This leads to a longer service life of the combustion chamber shingles. The longer service life is also due to the fact that a more uniform cooling of the shingles takes place and that the high temperature gradients known from the prior art are avoided.
  • connection with the fastener is ensured by means of the clamping effect occurring by a force flow in the "cold" area. This means that the thermal and mechanical stresses that occur in the area of the shingles and the shingles attachment, do not work together. This is a significant advantage of the solution according to the invention.
  • the Mischluftleitrohr can be formed according to the invention either as a separate part or in one piece with the shingle. In a separate Mischluftleitrohr it may be beneficial that the Effusionsbohrungen in Misch Kunststoffleitrohr are easier and more accurate to produce, so that the Mischluftleitrohr can be better cooled.
  • the fastener may have different thread sizes, depending on the particular sizes and the specific conditions of use. This results in an optimal adaptability of the solution according to the invention to different requirements.
  • the Beer maltationsaus fundamentalungen (Effusionskühlbohrungen) can be formed in the solution according to the invention perpendicular to the median plane or inclined.
  • the invention offers a variety of customization options to the respective design specifications.
  • Another, essential advantage of the invention is that at the attachment point, to which the shingle is fastened by means of the fastening element to the combustion chamber wall, results in a very low clearance. This allows a very good positioning between the shingle and the combustion chamber wall achieved become. This in turn influences the assignment of the air passage recesses, so that they can be arranged in a favorable association with each other.
  • 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 succession an air inlet 11, a fan 12 circulating in a housing, 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 intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 extending radially outward from a rotatable drum or disc 26, which are coupled to hubs 27 of the high-pressure turbine 16 and the intermediate-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 blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 and 3 each show perspective simplified partial sectional views.
  • a combustion chamber wall 29 is shown, on which a shingle 30 is mounted at a distance from the combustion chamber wall 29.
  • the combustion chamber wall 29 has a circular recess 32 in the region of the attachment of the shingle. This recess may also be out of round, for example polygonal.
  • the shingle 30 is provided with an annular flange 31, which is integrally formed on the shingle 30 and is dimensioned so that it according to Fig. 2 the recess 32 passes through.
  • the annular flange is provided on its inside with a thread 34.
  • the shingle In the interior of the annular flange 31, the shingle has on its wall a plurality of Lucas gutsausbrookonne 38. This makes it possible to perform cooling air through the shingle 30 and, as described, form a cooling air film on the hot side of the shingle 30.
  • the Fig. 2 further shows an embodiment of a fastener 33 according to the invention.
  • This is in the form of a round insert body which has a cup-like structure.
  • the fastening element 33 has an external thread which can be screwed to the thread 34 of the annular flange 31.
  • the fastening element 33 is provided with a plurality of Lucas gutsaus traditions 37, through which cooling air to the outside of the shingle 30 can be supplied.
  • the fastener 33 is firmly bolted to the annular flange 31 of the shingle 30.
  • the annular flange 31 is sealingly against the edge of the recess 32 of the combustion chamber wall 29, so that the undesirable passage of leakage flow is avoided.
  • the sealing effect is also ensured by the fact that the fastening element 33, as in Fig. 2 shown, also against the outside of the combustion chamber wall 29 abuts.
  • the outer diameter of the protruding portion of the annular flange 31 and the inner diameter of the recess 32 allow play, so that manufacturing inaccuracies or thermal expansions can be compensated without affecting the sealing effect.
  • a tight clearance fit at individual attachment points can positively influence the positioning of the shingle and thus the mixing air openings within the combustion chamber. Furthermore, a more accurate alignment of the cooling air holes in the shingle support to the cooling air holes in the shingle is possible.
  • the Fig. 3 shows a representation analog Fig. 2 , The same parts are provided with the same reference numbers.
  • the fastening element 33 is tubular. It is not bolted with its thread 34 against the annular flange 31, but clamps the annular flange 31 against a Mischluftleitrohr (chute), which is provided with an internal thread.
  • the fastening element 33 is thus in positive engagement with the Mischluftleitrohr and thus clamps the edge region of the recess 32 of the combustion chamber wall 29 and the annular flange 31 in sealing contact.
  • Mischluftleitrohr 35 it is possible to produce the Mischluftleitrohr 35 in a simple, cost-effective design and stored on the combustion chamber wall 29 and the shingle 30.
  • An optimized design of the inflow region 39 of the fastening element 33 ensures optimized flow guidance.
  • the 4 and 5 show a schematic representation of another embodiment of the invention.
  • the same parts are provided with the same reference numbers.
  • the fastening element 33 is provided with tool engagement means 40 on its outer contour. These can be in the form of a hexagon or other polygonal design or in the form of Holes or the like may be formed for engagement with a suitable tool.
  • the Fig. 5 shows an embodiment in which the Mischluftleitrohr 35 is integrally formed with the shingle 30. By screwing the shingle 30 thus the Mischluftleitrohr 35 is also attached.

Abstract

The arrangement has a combustion chamber wall that is provided with tiles fastened to combustion chamber wall at a distance from the latter. The tile is provided with an annular flange arranged on its side assigned to the combustion chamber wall. The flange is dimensioned to match a recess of the combustion chamber wall and fastened to the combustion chamber wall by fastening element which engages in the combustion chamber wall.

Description

Die Erfindung bezieht sich auf eine Schindelbefestigungsanordnung einer Gasturbinenbrennkammer gemäß den Merkmalen des Oberbegriffs des Anspruchs 1.The invention relates to a shingle fastening arrangement of a gas turbine combustor according to the features of the preamble of claim 1.

Insbesondere bezieht sich die Erfindung auf eine Brennkammer einer Gasturbine, wobei an einer Brennkammerwand Schindeln befestigt sind, welche einen Abstand zu der Brennkammerwand aufweisen.In particular, the invention relates to a combustion chamber of a gas turbine, wherein on a combustion chamber wall shingles are attached, which have a distance from the combustion chamber wall.

Bei derartigen sogenannten zweiwandigen Brennkammern ist es bekannt, die Schindeln mittels Gewindestiften an der Brennkammerwand bzw. dem Schindelträger zu befestigen. Die Gewindestifte sind üblicherweise einstückig mit der Schindel ausgebildet. Diese Ausgestaltung wird insbesondere auch für Prall-Effusions-Schindeln verwendet. Bei derartigen Schindeln werden um den Gewindestift oder Bolzen herum Abstandshalter eingesetzt, um eine gleichmäßige Belastung der Bolzen oder Gewindestifte zu erzielen und um sowohl eine gute Abdichtung als auch einen gleichmäßigen Abstand zwischen der Schindel und dem Schindelträger sicherzustellen.In such so-called two-walled combustion chambers, it is known to fasten the shingles by means of threaded pins on the combustion chamber wall or the shingle support. The grub screws are usually formed integrally with the shingle. This embodiment is used in particular for impact-effusion shingles. In such shingles, spacers are used around the grub screw or bolt to achieve even loading of the bolts or grub screws and to ensure both good sealing and even spacing between the shingle and the shingle support.

Weiterhin ist es bei Brennkammern bekannt, einen großen Teil der Verbrennungsluft über Mischluftöffnungen in die Brennkammer einzuleiten. Dabei werden zur gezielten Ausrichtung des Luftstroms Luftleitelemente oder Luftleitrohre verwendet (chutes). Die Mischluftöffnungen werden entweder in der Brennkammerwand integriert bzw. daran befestigt oder sie sind in die Schindeln integriert. Derartige Schindeln mit integrierten Mischluftöffnungen und Mischluftleitelementen werden üblicherweise mittels eines Gießverfahrens hergestellt.Furthermore, it is known in combustion chambers to introduce a large part of the combustion air via mixed air openings in the combustion chamber. In this case, air guide elements or air guide tubes are used for targeted alignment of the air flow (chutes). The mixing air openings are either integrated in the combustion chamber wall or attached thereto or they are integrated in the shingles. Such shingles with integrated mixed air openings and Mischluftleitelementen are usually produced by means of a casting process.

Bei Brennkammern ist es wünschenswert, die Schindeln über die gesamte Fläche gleichmäßig zu kühlen. Bei den oben beschriebenen Ausgestaltungen mit Gewindestiften bzw. Bolzen und Abstandshaltern ergibt sich jedoch der Nachteil, dass keine effektive Prall-Effusions-Kühlung erfolgen kann. Der Grund dafür liegt darin, dass die Bolzen und Abstandshalter in ihrem Befestigungsbereich keine Ausbildung von Kühlluftdurchtrittsausnehmungen ermöglichen. Somit entstehen hohe Temperaturen und Temperaturgradienten im Bereich der Befestigung der Schindeln an der Brennkammer. Dies wiederum beeinflusst die Dauerfestigkeit der Schindeln negativ. Dieser Nachteil wird, wie erwähnt, insbesondere dadurch hervorgerufen, dass im Bereich der integrierten Bolzen oder Gewindestifte bzw. der Abstandshalter und der Mischluftleitelemente keine Effusionsbohrungen mittels Laser eingebracht werden können, da hierdurch die integrierten Bauteile beschädigt würden. Dies führt dazu, dass an der heißen Seite der Schindel der Kühlluftfilm beeinträchtigt oder unterbrochen wird. Dies führt zu den erwähnten lokalen hohen Temperaturen und Temperaturgradienten.For combustors, it is desirable to evenly cool the shingles over the entire area. In the embodiments described above with threaded pins or bolts and spacers, however, there is the disadvantage that no effective impact-effusion cooling can take place. The reason for this is that the bolts and spacers do not allow formation of cooling air passage recesses in their attachment area. This results in high temperatures and temperature gradients in the region of attachment of the shingles to the combustion chamber. This, in turn, adversely affects the fatigue strength of the shingles. This disadvantage is, as mentioned, in particular caused by the fact that no effusion holes can be introduced by means of laser in the area of the integrated bolts or setscrews or the spacers and Mischluftleitelemente, as this would damage the integrated components. As a result, the cooling air film is impaired or interrupted on the hot side of the shingle. This leads to the mentioned local high temperatures and temperature gradients.

Der Erfindung liegt die Aufgabe zugrunde, eine Schindelbefestigungsanordnung einer Gasturbinenbrennkammer zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit die Nachteile des Standes der Technik vermeidet und eine gute Kühlung, insbesondere der Schindel, ermöglicht.The invention has for its object to provide a Schindelbefestigungsanordnung a gas turbine combustor, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and good cooling, especially the shingles allows.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die weiteren Ansprüche beschreiben weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the feature combination of claim 1, the further claims describe further advantageous embodiments of the invention.

Erfindungsgemäß ist somit vorgesehen, dass die Schindel mit einem an ihrer der Brennkammerwand zugewandten Seite angeordneten Ringflansch versehen ist. Dieser Ringflansch ist passend zu einer Ausnehmung der Brennkammerwand dimensioniert und greift entweder in diese Ausnehmung ein oder liegt bündig mit dem Rand der Ausnehmung an der Brennkammerwand an. Mittels eines Befestigungselements ist die Schindel mit der Brennkammerwand verbunden. Das Befestigungselement durchgreift dabei die Ausnehmung der Brennkammerwand und ist mechanisch mit dem Ringflansch verbunden. Diese Verbindung mit dem Ringflansch kann entweder direkt erfolgen. Hierzu weist der Ringflansch an seiner Innenseite ein Gewinde auf, welches sich im Eingriff mit einem Gewindeansatz des Befestigungselements befindet. Als Alternative hierzu ist es erfindungsgemäß auch möglich, ein Mischluftrohr zu verwenden, welches mit einem Innengewinde versehen ist und mit dem Befestigungselement verschraubt ist. Bei dieser Ausgestaltung der Erfindung wird der Ringflansch zwischen dem Mischluftleitrohr und dem Befestigungselement geklemmt, so dass die Schindel fest gegen die Brennkammerwand geklemmt wird.According to the invention, it is thus provided that the shingle is provided with an annular flange arranged on its side facing the combustion chamber wall. This annular flange is dimensioned to fit a recess of the combustion chamber wall and engages either in this recess or is flush with the edge of the recess on the combustion chamber wall. By means of a fastening element, the shingle is connected to the combustion chamber wall. The fastener extends through the recess of the combustion chamber wall and is mechanically connected to the annular flange. This connection with the annular flange can be done either directly. For this purpose, the annular flange on its inside a thread, which is in engagement with a threaded extension of the fastener. As an alternative, it is also possible according to the invention to use a mixed-air tube which is provided with an internal thread and is screwed to the fastening element. In this embodiment of the invention, the annular flange is clamped between the Mischluftleitrohr and the fastener, so that the shingle is firmly clamped against the combustion chamber wall.

Erfindungsgemäß ist das Befestigungselement rund ausgebildet. Es kann dabei, sofern kein Mischluftleitrohr verwendet wird, napfartig ausgestaltet sein. Dabei ist es besonders günstig, wenn im zentrischen Bereich der napfartigen Ausgestaltung des Befestigungselements Luftdurchtrittsausnehmungen vorgesehen sind, durch welche Kühlluft zu der Schindel zugeleitet werden kann. Die Schindel ist bevorzugterweise angrenzend an den zentrischen Bereich des Befestigungselements ebenfalls mit Luftdurchtrittsausnehmungen versehen, um Kühlluft zur heißen Seite der Schindel durchzuleiten.According to the invention, the fastening element is round. It may, unless a Mischluftleitrohr is used, be designed cup-like. That's it particularly favorable if in the central region of the cup-like configuration of the fastening element air passage recesses are provided, through which cooling air can be fed to the shingle. The shingle is also preferably provided adjacent to the central region of the fastener with air passage recesses to pass cooling air to the hot side of the shingle.

Mittels der erfindungsgemäßen Ausgestaltung ist es somit möglich, zwischen der Schindel und der Brennkammerwand (Schindelträger) eine effiziente Prall-Effusions-Kühlung zu realisieren. Hierdurch werden hohe Temperaturen im Bereich der Befestigung der Schindel an der Brennkammerwand vermieden. Der erfindungsgemäß vorgesehene Ringflansch kann dabei so dimensioniert werden, dass er nur eine sehr geringe Fläche der Schindel benötigt, so dass im Betrieb keine Störung des Kühlluftfilms auf der heißen Seite der Schindel erfolgt.By means of the embodiment according to the invention it is thus possible to realize an efficient impact-effusion cooling between the shingle and the combustion chamber wall (shingle support). As a result, high temperatures in the region of attachment of the shingle to the combustion chamber wall are avoided. The inventively provided annular flange can be dimensioned so that it requires only a very small area of the shingle, so that there is no disturbance of the cooling air film on the hot side of the shingle during operation.

Ein weiterer, wesentlicher Vorteil der erfindungsgemäßen Ausgestaltung liegt darin, dass der Ringflansch eine sehr geringe Höhe aufweisen kann. Durch die geringere Höhe des Ringflansches im Vergleich zu einem Gewindestift wird das Einbringen von Effusions - Kühlluftausnehmungen mittels z.B. Laser oder Elektronenstrahl weniger behindert. Hierdurch ist es möglich, Effusions-Kühlluftausnehmungen näher an die Verbindungsstelle, d.h., an den Ringflansch, heranzuführen. Auch hierdurch wird der Kühlfilm auf der heißen Seite der Schindel nicht oder nur geringfügig gestört.Another essential advantage of the embodiment according to the invention is that the annular flange can have a very small height. Due to the smaller height of the annular flange compared to a threaded pin, the introduction of effusion cooling air recesses by means of e.g. Laser or electron beam less obstructed. This makes it possible to bring effusion cooling air recesses closer to the joint, i.e. to the annular flange. As a result, the cooling film on the hot side of the shingle is not or only slightly disturbed.

Die erfindungsgemäße Schindelbefestigungsanordnung zeichnet sich durch eine Reihe erheblicher Vorteile aus. Zum einen ist es möglich, eine geringere Bauhöhe zu realisieren. Hierdurch ist es in der Folge möglich, kleinere Brennkammergehäuse oder größere Brennkammervolumen bei gleichem Bauraum zu ermöglichen. Dies führt zu einem geringeren Gewicht der Brennkammer sowie zu einer Einsparung an Material und Fertigungskosten. Weiterhin ist es erfindungsgemäß möglich, den Bereich der Schindelbefestigung effektiv zu kühlen. Hierdurch werden heiße Bereiche, wie sie beim Stand der Technik auftreten, vermieden. Dies führt zu einer höheren Lebensdauer der Brennkammerschindeln. Die höhere Lebensdauer ergibt sich auch dadurch, dass eine gleichmäßigere Kühlung der Schindeln erfolgt und dass die aus dem Stand der Technik bekannten hohen Temperaturgradienten vermieden werden. Ursache hierfür ist die im Wesentlichen ungestörte Ausbildung des Kühlfilms durch die erfindungsgemäße Schindelbefestigungsanordnung. Auch die erfindungsgemäß mögliche Kombination der Schindelbefestigung mit den Mischluftleitrohren (chutes) führt zu einer Optimierung der Kühlung und zu geringeren Flächen, die für die Kühlung erforderlich sind. Es ergibt sich somit eine geringere ungekühlte Fläche, Auch dies führt, wie erwähnt, zur Vermeidung von hohen Temperaturgradienten und resultiert in einer Erhöhung der Lebensdauer.The shingle attachment arrangement according to the invention is characterized by a number of significant advantages. On the one hand, it is possible to realize a lower overall height. As a result, it is possible in the sequence to allow smaller combustion chamber or larger combustion chamber volume with the same space. This leads to a lower weight of the combustion chamber and to a saving in material and manufacturing costs. Furthermore, it is possible according to the invention to effectively cool the area of the shingle attachment. As a result, hot areas, as they occur in the prior art, avoided. This leads to a longer service life of the combustion chamber shingles. The longer service life is also due to the fact that a more uniform cooling of the shingles takes place and that the high temperature gradients known from the prior art are avoided. The reason for this is the im Essentially undisturbed formation of the cooling film by the invention Schindelbefestigungsanordnung. The invention also possible combination of shingles with the Mischluftleitrohren (chutes) leads to an optimization of the cooling and to smaller areas that are required for cooling. This results in a lower uncooled area, this also leads, as mentioned, to avoid high temperature gradient and results in an increase in the life.

Bei der erfindungsgemäßen Ausgestaltung ist weiterhin zu berücksichtigen, dass die Verbindung mit dem Befestigungselement mittels der auftretenden Klemmwirkung durch einen Kraftfluss im "kalten" Bereich sichergestellt wird. Dies bedeutet, dass die thermischen und mechanischen Belastungen, welche im Bereich der Schindel und der Schindelbefestigung auftreten, nicht gemeinsam wirken. Dies ist ein erheblicher Vorteil der erfindungsgemäßen Lösung.In the embodiment of the invention is further considered that the connection with the fastener is ensured by means of the clamping effect occurring by a force flow in the "cold" area. This means that the thermal and mechanical stresses that occur in the area of the shingles and the shingles attachment, do not work together. This is a significant advantage of the solution according to the invention.

Das Mischluftleitrohr kann erfindungsgemäß entweder als separates Teil oder einstückig mit der Schindel ausgebildet sein. Bei einem separaten Mischluftleitrohr kann es günstig sein, dass die Effusionsbohrungen im Mischluftleitrohr einfacher und genauer herstellbar sind, so dass auch das Mischluftleitrohr besser gekühlt werden kann.The Mischluftleitrohr can be formed according to the invention either as a separate part or in one piece with the shingle. In a separate Mischluftleitrohr it may be beneficial that the Effusionsbohrungen in Mischluftleitrohr are easier and more accurate to produce, so that the Mischluftleitrohr can be better cooled.

Das Befestigungselement kann unterschiedliche Gewindegrößen aufweisen, abhängig von den jeweiligen Baugrößen und den speziellen Einsatzbedingungen. Hierdurch ergibt sich eine optimale Anpassbarkeit der erfindungsgemäßen Lösung an unterschiedliche Anforderungen.The fastener may have different thread sizes, depending on the particular sizes and the specific conditions of use. This results in an optimal adaptability of the solution according to the invention to different requirements.

Die Luftdurchtrittsausnehmungen (Effusionskühlbohrungen) können bei der erfindungsgemäßen Lösung senkrecht zur Mittelebene oder geneigt ausgebildet werden. Insofern bietet die Erfindung eine Vielzahl von Anpassungsmöglichkeiten an die jeweiligen konstruktiven Vorgaben.The Luftdurchtrittsausnehmungen (Effusionskühlbohrungen) can be formed in the solution according to the invention perpendicular to the median plane or inclined. In this respect, the invention offers a variety of customization options to the respective design specifications.

Ein weiterer, wesentlicher Vorteil der Erfindung liegt darin, dass sich an der Befestigungsstelle, an welcher die Schindel mittels des Befestigungselements an der Brennkammerwand befestigt ist, ein sehr geringes Spiel ergibt. Hierdurch kann eine sehr gute Positionierung zwischen der Schindel und der Brennkammerwand erzielt werden. Dies wiederum beeinflusst die Zuordnung der Luftdurchtrittsausnehmungen, so dass diese in günstiger Zuordnung zueinander angeordnet werden können.Another, essential advantage of the invention is that at the attachment point, to which the shingle is fastened by means of the fastening element to the combustion chamber wall, results in a very low clearance. This allows a very good positioning between the shingle and the combustion chamber wall achieved become. This in turn influences the assignment of the air passage recesses, so that they can be arranged in a favorable association with each other.

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 vereinfachte perspektivische Teil-Schnittansicht eines erfindungsgemäßen Befestigungselements mit Luftdurchtrittsausnehmungen,
Fig. 3
eine Darstellung, analog Fig. 2, eines Ausführungsbeispiels eines erfindungsgemäßen Befestigungselements mit einem Mischluftleitrohr,
Fig. 4
eine Draufsicht auf ein weiteres Ausführungsbeispiel, und
Fig. 5
eine Schnittansicht des in Fig. 4 gezeigten Ausführungsbeispiels.
In the following the invention will be described by means of embodiments 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 perspective partial sectional view of a fastener according to the invention with air passage recesses,
Fig. 3
a representation, analog Fig. 2 , an embodiment of a fastener according to the invention with a Mischluftleitrohr,
Fig. 4
a plan view of a further embodiment, and
Fig. 5
a sectional view of the in Fig. 4 shown embodiment.

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 succession an air inlet 11, a fan 12 circulating in a housing, 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 Zwischendruckkompressor 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 Triebwerksgehäuse 21 in einem 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 intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude. The compressors further include an array of compressor blades 22 extending radially outward from a rotatable drum or disc 26, which are coupled to hubs 27 of the high-pressure turbine 16 and the intermediate-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 Turbinenschaufeln 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 Turbinenlaufschaufeln 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 blades 24 projecting outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.

Die Fig. 2 und 3 zeigen jeweils perspektivische vereinfachte Teil-Schnittansichten. Dabei ist eine Brennkammerwand 29 dargestellt, an welcher mit einem Abstand zur Brennkammerwand 29 eine Schindel 30 gelagert ist. Erfindungsgemäß weist die Brennkammerwand 29 im Bereich der Befestigung der Schindel eine kreisrunde Ausnehmung 32 auf. Diese Ausnehmung kann auch unrund sein, beispielsweise polygonal. Die Schindel 30 ist mit einem Ringflansch 31 versehen, welcher einstückig an der Schindel 30 ausgebildet ist und so dimensioniert ist, dass er gemäß Fig. 2 die Ausnehmung 32 durchgreift. Der Ringflansch ist an seiner Innenseite mit einem Gewinde 34 versehen. Im Innenbereich des Ringflansches 31 weist die Schindel an ihrer Wandung eine Vielzahl von Luftdurchtrittsausnehmungen 38 auf. Hierdurch ist es möglich, Kühlluft durch die Schindel 30 durchzuführen und, wie beschrieben, einen Kühlluftfilm auf der heißen Seite der Schindel 30 auszubilden.The Fig. 2 and 3 each show perspective simplified partial sectional views. In this case, a combustion chamber wall 29 is shown, on which a shingle 30 is mounted at a distance from the combustion chamber wall 29. According to the invention, the combustion chamber wall 29 has a circular recess 32 in the region of the attachment of the shingle. This recess may also be out of round, for example polygonal. The shingle 30 is provided with an annular flange 31, which is integrally formed on the shingle 30 and is dimensioned so that it according to Fig. 2 the recess 32 passes through. The annular flange is provided on its inside with a thread 34. In the interior of the annular flange 31, the shingle has on its wall a plurality of Luftdurchtrittsausnehmungen 38. This makes it possible to perform cooling air through the shingle 30 and, as described, form a cooling air film on the hot side of the shingle 30.

Die Fig. 2 zeigt weiterhin ein Ausführungsbeispiel eines erfindungsgemäßen Befestigungselements 33. Dieses ist in Form eines runden Einsatzkörpers ausgebildet, welcher eine napfartige Struktur hat. Das Befestigungselement 33 weist ein Außengewinde auf, welches mit dem Gewinde 34 des Ringflansches 31 verschraubbar ist. Im zentrischen Bereich ist das Befestigungselement 33 mit einer Vielzahl von Luftdurchtrittsausnehmungen 37 versehen, durch welche Kühlluft zur Außenseite der Schindel 30 zugeführt werden kann.The Fig. 2 further shows an embodiment of a fastener 33 according to the invention. This is in the form of a round insert body which has a cup-like structure. The fastening element 33 has an external thread which can be screwed to the thread 34 of the annular flange 31. In the central region, the fastening element 33 is provided with a plurality of Luftdurchtrittsausnehmungen 37, through which cooling air to the outside of the shingle 30 can be supplied.

Wie die Darstellung der Fig. 2 zeigt, ist das Befestigungselement 33 fest mit dem Ringflansch 31 der Schindel 30 verschraubt. Dabei liegt der Ringflansch 31 dichtend gegen den Rand der Ausnehmung 32 der Brennkammerwand 29 an, so dass der unerwünschte Durchtritt von Leckageströmung vermieden wird. Die Dichtwirkung wird auch dadurch gewährleistet, dass das Befestigungselement 33, wie in Fig. 2 gezeigt, ebenfalls gegen die Außenseite der Brennkammerwand 29 anliegt. Bei der in Fig. 2 gezeigten Konstruktion ist weiterhin ersichtlich, dass der Außendurchmesser des vorstehenden Bereichs des Ringflansches 31 und der Innendurchmesser der Ausnehmung 32 ein Spiel zulassen, so dass Fertigungsungenauigkeiten oder Wärmeausdehnungen kompensiert werden können, ohne dass die Dichtwirkung beeinflusst wird. Eine enge Spielpassung an einzelnen Befestigungspunkten kann die Positionierung der Schindel und damit der Mischluftöffnungen innerhalb der Brennkammer positiv beeinflussen. Weiterhin ist eine genauere Ausrichtung der Kühlluftbohrungen im Schindelträger zu den Kühlluftbohrungen in der Schindel möglich.Like the representation of the Fig. 2 shows, the fastener 33 is firmly bolted to the annular flange 31 of the shingle 30. In this case, the annular flange 31 is sealingly against the edge of the recess 32 of the combustion chamber wall 29, so that the undesirable passage of leakage flow is avoided. The sealing effect is also ensured by the fact that the fastening element 33, as in Fig. 2 shown, also against the outside of the combustion chamber wall 29 abuts. At the in Fig. 2 As shown, it can further be seen that the outer diameter of the protruding portion of the annular flange 31 and the inner diameter of the recess 32 allow play, so that manufacturing inaccuracies or thermal expansions can be compensated without affecting the sealing effect. A tight clearance fit at individual attachment points can positively influence the positioning of the shingle and thus the mixing air openings within the combustion chamber. Furthermore, a more accurate alignment of the cooling air holes in the shingle support to the cooling air holes in the shingle is possible.

Die Fig. 3 zeigt eine Darstellung analog Fig. 2. Gleiche Teile sind mit gleichen Bezugsziffern versehen. Bei der Darstellung der Fig. 3 ist das Befestigungselement 33 rohrförmig ausgebildet. Es ist mit seinem Gewinde 34 nicht gegen den Ringflansch 31 verschraubt, sondern klemmt den Ringflansch 31 gegen ein Mischluftleitrohr (chute), welches mit einem Innengewinde versehen ist. Das Befestigungselement 33 befindet sich somit in formschlüssigem Eingriff mit dem Mischluftleitrohr und klemmt somit den Randbereich der Ausnehmung 32 der Brennkammerwand 29 und den Ringflansch 31 in dichtender Anlage. Somit ist es möglich, das Mischluftleitrohr 35 in einfacher, kostengünstiger Ausgestaltung herzustellen und an der Brennkammerwand 29 bzw. der Schindel 30 zu lagern. Durch eine optimierte Ausgestaltung des Einströmbereichs 39 des Befestigungselements 33, beispielsweise durch geeignete Abrundung, wird eine optimierte Strömungsführung gewährleistet.The Fig. 3 shows a representation analog Fig. 2 , The same parts are provided with the same reference numbers. In the presentation of Fig. 3 the fastening element 33 is tubular. It is not bolted with its thread 34 against the annular flange 31, but clamps the annular flange 31 against a Mischluftleitrohr (chute), which is provided with an internal thread. The fastening element 33 is thus in positive engagement with the Mischluftleitrohr and thus clamps the edge region of the recess 32 of the combustion chamber wall 29 and the annular flange 31 in sealing contact. Thus, it is possible to produce the Mischluftleitrohr 35 in a simple, cost-effective design and stored on the combustion chamber wall 29 and the shingle 30. An optimized design of the inflow region 39 of the fastening element 33, for example by suitable rounding, ensures optimized flow guidance.

Die Fig. 4 und 5 zeigen in schematischer Darstellung ein weiteres Ausführungsbeispiel der Erfindung. Gleiche Teile sind mit gleichen Bezugsziffern versehen. Bei der in Fig. 4 gezeigten Ansicht ist zu erkennen, dass das Befestigungselement 33 an seiner Außenkontur mit Werkzeugeingriffsmitteln 40 versehen ist. Diese können in Form eines Sechskants oder einer anderen polygonalen Ausgestaltung oder in Form von Bohrungen oder Ähnlichem zum Eingriff mit einem geeigneten Werkzeug ausgebildet sein.The 4 and 5 show a schematic representation of another embodiment of the invention. The same parts are provided with the same reference numbers. At the in Fig. 4 As shown, it can be seen that the fastening element 33 is provided with tool engagement means 40 on its outer contour. These can be in the form of a hexagon or other polygonal design or in the form of Holes or the like may be formed for engagement with a suitable tool.

Die Fig. 5 zeigt eine Ausgestaltung, bei welcher das Mischluftleitrohr 35 einstückig mit der Schindel 30 ausgebildet ist. Durch ein Verschrauben der Schindel 30 wird somit das Mischluftleitrohr 35 ebenfalls befestigt.The Fig. 5 shows an embodiment in which the Mischluftleitrohr 35 is integrally formed with the shingle 30. By screwing the shingle 30 thus the Mischluftleitrohr 35 is also attached.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
TriebwerksachseEngine axis
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
TriebwerksgehäuseEngine casing
2222
KompressorlaufschaufelnCompressor blades
2323
Leitschaufelnvanes
2424
Turbinenschaufelnturbine blades
2626
Kompressortrommel oder -ScheibeCompressor drum or disc
2727
TurbinenrotornabeTurbinenrotornabe
2828
Auslasskonusoutlet cone
2929
Brennkammerwandcombustion chamber wall
3030
Schindelshingle
3131
Ringflanschannular flange
3232
Ausnehmungrecess
3333
Befestigungselementfastener
3434
Gewindethread
3535
MischluftleitrohrMischluftleitrohr
3636
zentrischer Bereichcentric area
3737
LuftdurchtrittsausnehmungLuftdurchtrittsausnehmung
3838
LuftdurchtrittsausnehmungLuftdurchtrittsausnehmung
3939
Einströmbereichinflow
4040
WerkzeugeingriffsmittelTool engagement means

Claims (10)

Schindelbefestigungsanordnung einer Gasturbinenbrennkammer (15) mit einer Brennkammerwand (29) und mit in einem Abstand an dieser befestigten Schindeln (30), dadurch gekennzeichnet, dass die Schindel (30) mit einem an ihrer der Brennkammerwand (29) zugeordneten Seite angeordneten Ringflansch (31) versehen ist, welcher passend zu einer Ausnehmung (32) der Brennkammerwand (29) dimensioniert und mittels eines die Brennkammerwand (29) durchgreifenden Befestigungselements (33) an der Brennkammerwand (29) befestigt ist.Shingle fastening arrangement of a gas turbine combustion chamber (15) with a combustion chamber wall (29) and shingles (30) attached thereto at a distance, characterized in that the shingle (30) is provided with an annular flange (31) arranged at its side of the combustion chamber wall (29). is provided, which fits to a recess (32) of the combustion chamber wall (29) and by means of a combustion chamber wall (29) by cross-fastener (33) on the combustion chamber wall (29) is attached. Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass das Befestigungselement (33) mittels eines Gewindes (34) mit dem Ringflansch (31) verschraubt ist.Arrangement according to claim 1, characterized in that the fastening element (33) by means of a thread (34) with the annular flange (31) is screwed. Anordnung nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass das Befestigungselement (33) mittels eines Gewindes (34) mit einem Mischluftleitrohr (35) unter Klemmung des Ringflansches (31) verschraubt ist.Arrangement according to claim 1 or 2, characterized in that the fastening element (33) by means of a thread (34) with a Mischluftleitrohr (35) under clamping of the annular flange (31) is screwed. Anordnung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das Befestigungselement (33) rund ausgebildet ist und im zentrischen Bereich (36) mit Luftdurchtrittsausnehmungen (37) versehen ist.Arrangement according to one of claims 1 to 3, characterized in that the fastening element (33) is round and is provided in the central region (36) with Luftdurchtrittsausnehmungen (37). Anordnung nach Anspruch 4, dadurch gekennzeichnet, dass die Schindel (30) zumindest innerhalb des Ringflansches (31) mit Luftdurchtrittsausnehmungen (38) versehen ist.Arrangement according to claim 4, characterized in that the shingle (30) is provided at least within the annular flange (31) with air passage recesses (38). Schindelbefestigungsanordnung einer Gasturbinenbrennkammer (15) mit einer Brennkammerwand (29) und mit in einem Abstand an dieser befestigten Schindeln (30), dadurch gekennzeichnet, dass die Brennkammerwand (29) mit zumindest einer kreisrunden Ausnehmung (32) versehen ist, durch welche von der der Schindel (30) abgewandten Seite aus ein rund ausgebildetes Befestigungselement (33) durchgeführt und unmittelbar oder mittelbar mit einem an der Schindel (30) ausgebildeten Ringflansch (31) verbunden ist.Shingle attachment arrangement of a gas turbine combustion chamber (15) having a combustion chamber wall (29) and shingles (30) attached thereto at a distance, characterized in that the combustion chamber wall (29) is provided with at least one circular recess (32) through which the Shingle (30) facing away from a round shaped fastener (33) performed and directly or indirectly connected to an on the shingle (30) formed annular flange (31). Anordnung nach Anspruch 6, dadurch gekennzeichnet, dass das Befestigungselement (33) rohrartig ausgebildet und unter Klemmung des Ringflansches (31) mit einem Mischluftleitrohr (35) verschraubt ist.Arrangement according to claim 6, characterized in that the fastening element (33) is tubular and is screwed under clamping of the annular flange (31) with a Mischluftleitrohr (35). Anordnung nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass das Befestigungselement (33) napfförmig ausgebildet ist, an seinem mittleren Bereich mit Luftdurchtrittsausnehmungen (37) versehen ist und mit einem Gewinde (34) des Ringflansches (31) verschraubt ist.Arrangement according to claim 6 or 7, characterized in that the fastening element (33) is cup-shaped, at its central region with Luftdurchtrittsausnehmungen (37) is provided and with a thread (34) of the annular flange (31) is screwed. Anordnung nach Anspruch 8, dadurch gekennzeichnet, dass die Schindel (30) innerhalb des Ringflansches (31) mit Luftdurchtrittsausnehmungen (38) versehen ist.Arrangement according to claim 8, characterized in that the shingle (30) is provided within the annular flange (31) with air passage recesses (38). Anordnung nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass das Befestigungselement (33) an seiner Außenseite mit Werkzeugeingriffsmitteln (40) versehen ist.Arrangement according to one of claims 1 to 9, characterized in that the fastening element (33) is provided on its outer side with a tool engagement means (40).
EP13191950.8A 2012-11-28 2013-11-07 Shingle attachment assembly of a gas turbine combustion chamber Not-in-force EP2738470B1 (en)

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016062977A1 (en) * 2014-10-24 2016-04-28 Aircelle Assembly of a fixed inner structure of a nacelle of a turbojet and a thermal protection element
EP3043113A1 (en) * 2015-01-12 2016-07-13 A.S.EN. Ansaldo Sviluppo Energia S.r.l. Fastening device for thermoinsulating tile of gas turbine combustion chamber
DE102016217876A1 (en) 2016-09-19 2018-03-22 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber wall of a gas turbine with attachment of a combustion chamber shingle
US10060626B2 (en) 2015-12-14 2018-08-28 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber with a shingle attachment by means of catching elements
EP3385622A1 (en) * 2017-04-03 2018-10-10 United Technologies Corporation Gas turbine combustion panel grommet
DE102018204453A1 (en) 2018-03-22 2019-09-26 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
EP3587928A1 (en) * 2018-06-28 2020-01-01 United Technologies Corporation Combustor shell attachment

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2735796B1 (en) * 2012-11-23 2020-01-01 Ansaldo Energia IP UK Limited Wall of a hot gas path component of a gas turbine and method for enhancing operational behaviour of a gas turbine
US10100737B2 (en) * 2013-05-16 2018-10-16 Siemens Energy, Inc. Impingement cooling arrangement having a snap-in plate
US10386070B2 (en) * 2013-12-23 2019-08-20 United Technologies Corporation Multi-streamed dilution hole configuration for a gas turbine engine
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US10533747B2 (en) * 2017-03-30 2020-01-14 General Electric Company Additively manufactured mechanical fastener with cooling fluid passageways
US20180283689A1 (en) * 2017-04-03 2018-10-04 General Electric Company Film starters in combustors of gas turbine engines
US11566787B2 (en) * 2020-04-06 2023-01-31 Rolls-Royce Corporation Tile attachment scheme for counter swirl doublet

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2173891A (en) * 1985-04-05 1986-10-22 Agency Ind Science Techn Gas turbine combustor
EP1351022A2 (en) * 2002-04-02 2003-10-08 Rolls-Royce Deutschland Ltd & Co KG Air passage for turbine combustor with shingles
EP1712840A1 (en) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Heat shield assembly with fixation bolt
US20080127652A1 (en) * 2004-12-16 2008-06-05 Heinrich Putz Heat Shield Element
US20110030378A1 (en) * 2009-08-05 2011-02-10 Rolls-Royce Plc Combustor tile mounting arrangement

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB647302A (en) * 1948-05-14 1950-12-13 Edgar Phillips Peregrine Improvements in or relating to linings for combustion chambers and the like
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
DE3664374D1 (en) * 1985-12-02 1989-08-17 Siemens Ag Heat shield arrangement, especially for the structural components of a gas turbine plant
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
US5144793A (en) * 1990-12-24 1992-09-08 United Technologies Corporation Integrated connector/airtube for a turbomachine's combustion chamber walls
DE19751299C2 (en) * 1997-11-19 1999-09-09 Siemens Ag Combustion chamber and method for steam cooling a combustion chamber
GB2380236B (en) * 2001-09-29 2005-01-19 Rolls Royce Plc A wall structure for a combustion chamber of a gas turbine engine
EP1389690B1 (en) * 2002-08-16 2007-01-03 Siemens Aktiengesellschaft Screw interiorly cooled

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2173891A (en) * 1985-04-05 1986-10-22 Agency Ind Science Techn Gas turbine combustor
EP1351022A2 (en) * 2002-04-02 2003-10-08 Rolls-Royce Deutschland Ltd & Co KG Air passage for turbine combustor with shingles
US20080127652A1 (en) * 2004-12-16 2008-06-05 Heinrich Putz Heat Shield Element
EP1712840A1 (en) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Heat shield assembly with fixation bolt
US20110030378A1 (en) * 2009-08-05 2011-02-10 Rolls-Royce Plc Combustor tile mounting arrangement

Cited By (12)

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WO2016062977A1 (en) * 2014-10-24 2016-04-28 Aircelle Assembly of a fixed inner structure of a nacelle of a turbojet and a thermal protection element
FR3027630A1 (en) * 2014-10-24 2016-04-29 Aircelle Sa ASSEMBLY OF INTERNAL FIXED STRUCTURE OF TURBOJET NACELLE AND THERMAL PROTECTION
US10001064B2 (en) 2014-10-24 2018-06-19 Safran Nacelles Assembly of an inner fixed structure of a turbojet engine nacelle and of a thermal protection
EP3043113A1 (en) * 2015-01-12 2016-07-13 A.S.EN. Ansaldo Sviluppo Energia S.r.l. Fastening device for thermoinsulating tile of gas turbine combustion chamber
US10060626B2 (en) 2015-12-14 2018-08-28 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber with a shingle attachment by means of catching elements
DE102016217876A1 (en) 2016-09-19 2018-03-22 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber wall of a gas turbine with attachment of a combustion chamber shingle
EP3385622A1 (en) * 2017-04-03 2018-10-10 United Technologies Corporation Gas turbine combustion panel grommet
DE102018204453A1 (en) 2018-03-22 2019-09-26 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
US11320144B2 (en) 2018-03-22 2022-05-03 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
DE102018204453B4 (en) 2018-03-22 2024-01-18 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto
EP3587928A1 (en) * 2018-06-28 2020-01-01 United Technologies Corporation Combustor shell attachment
US10808930B2 (en) 2018-06-28 2020-10-20 Raytheon Technologies Corporation Combustor shell attachment

Also Published As

Publication number Publication date
US9341372B2 (en) 2016-05-17
EP2738470B1 (en) 2015-05-27
US20140144146A1 (en) 2014-05-29
DE102012023297A1 (en) 2014-06-12

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