EP2360352A2 - Screw-free intermediate stage seal of a gas turbine - Google Patents
Screw-free intermediate stage seal of a gas turbine Download PDFInfo
- Publication number
- EP2360352A2 EP2360352A2 EP11001144A EP11001144A EP2360352A2 EP 2360352 A2 EP2360352 A2 EP 2360352A2 EP 11001144 A EP11001144 A EP 11001144A EP 11001144 A EP11001144 A EP 11001144A EP 2360352 A2 EP2360352 A2 EP 2360352A2
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- Prior art keywords
- outer ring
- inner ring
- ring
- holding elements
- assembly according
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- 238000007789 sealing Methods 0.000 claims description 13
- 230000014759 maintenance of location Effects 0.000 claims description 2
- 150000001875 compounds Chemical class 0.000 claims 1
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 description 7
- 238000006073 displacement reaction Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 210000004907 gland Anatomy 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 241000191291 Abies alba Species 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
Definitions
- the invention relates to an interstage seal arrangement of a gas turbine, and more particularly to a gas turbine having a screwless interstage seal construction.
- the prior art shows constructions in which the interstage seal assembly consists of two rings which are either individually secured to the vanes independently of each other or which are bolted together.
- Another known embodiment is the division into two half-rings, which must be mounted after screwing the rotor disks.
- split interstage seal rings an increased amount of processing is required. In particular, elaborate milling work is necessary. Such an assembly is matched with respect to their elements, so that individual elements (for example, half-rings) can not be replaced individually. Furthermore, such a system-inherently non-rotationally symmetrical construction is exposed during operation to asymmetrical thermal expansions, so that such components can deform from a circular shape into an oval shape. As a result, an increased cold gap may be required and thus result in increased leakage.
- the invention has for its object to provide an intermediate stage seal arrangement of a gas turbine of the type mentioned, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and in particular has good structural properties.
- the interstage seal arrangement has a (radially) outer ring, which is held both axially by guide vanes Also centered and thus stored, and a (radial) inner ring which is mounted on the outer ring comprises.
- the terms (radially) outer and (radial) inner refer to the axis of rotation or machine axis.
- front and rear reference is made to the direction of flow of the gas turbine, front thus means closer to the inlet region, while rear means closer to the outlet.
- each of the rings namely the outer ring and the inner ring, is provided with at least one sealing area to perform the function of an interstage seal arrangement.
- the invention provides that the inner ring on the outer ring by at least three radial tongue and groove connections, referred to below Radialnutenzentritation centered and is secured against rotation in the circumferential direction.
- the planes of symmetry of all tongue and groove joints must all contain the main axis of rotation of the components involved to prevent deformation or damage. This principle corresponds to the state of the art and is u.a. also used for the centering of the outer ring by the vanes. It allows different thermal expansions of the components involved while ensuring coaxiality.
- the circumferential groove in the outer ring can be designed for inserting retaining elements.
- the circumferential groove is provided either over the entire peripheral region or over part of its circumference with a larger axial width, which makes it possible to introduce additional holding elements in addition to the strip of the guide vane.
- additional holding elements At the periphery, for example, three such holding elements are provided which are sufficient to secure the inner ring against axial slipping when the engine is at a standstill.
- the outer ring and / or the inner ring is provided at the respective contact area with a ring bead-shaped sealing projection.
- inwardly facing retaining elements which are formed on the strip of the vane itself, either as pins which are pressed into radial bores of the strip, or as extensions of portions of the strip in the radial direction ,
- retaining elements are pressed into radial holes of the outer ring and these pin-like holding elements take over the retention function for the inner ring.
- the pin-like holding elements can be designed so that they ensure both the centering between guide vanes and outer ring and between the outer and inner ring.
- the Fig. 1 shows a first embodiment in which an outer interstage seal ring 1 and an inner interstage seal ring 3 are provided, which respectively include respective sealing portions 4, 5, 6.
- an outer interstage seal ring 1 and an inner interstage seal ring 3 are provided, which respectively include respective sealing portions 4, 5, 6.
- sealing portions 4, 5, 6 With regard to the dimensioning of the construction of the sealing regions 4, 5, 6, reference may be made to the prior art.
- the outer ring 1 comprises a circumferentially extending, radially outwardly open groove 12, in which a radially inwardly facing bar 11 of a foot of a guide vane 2 is inserted.
- the guide vanes 2 are formed according to the prior art and segmented in the circumferential direction, wherein in each case a plurality of guide vanes 2 may have a common foot 16.
- the Fig. 1 to 3 further show a disc 17 of a stage 1 of a turbine with rotor blades 19, and a disc 18 of a stage 2, which is located downstream of the intermediate stage seal assembly according to the invention, with rotor blades 20.
- the discs 17, 18 and the rotor blades 19, 20 can the state the technique be referenced.
- the outer ring 1 comprises a circumferentially extending, radially outwardly open groove 12 (see above), which is provided in the axial direction with an additional, widening groove 15, which merges into a recess 14 which extends radially inwardly opens.
- a holding element 7 is inserted, which (see Fig. 2 ) Is T-shaped and the foot 21 passes through the recess 14. The Retaining element 7 is held by the strip 11 after its assembly and thus extends with its foot radially inwards.
- the inner ring 3 Radially inward to the outer ring 1, the inner ring 3 is arranged. This rests against an annular projection 10 of the outer ring 1 and is thus supported in the axial direction.
- the annular projection 10 thus forms an abutment leg and fixes the inner ring 3, wherein the inner ring 3 is provided on its radial outer side with a space for thermal expansion relative to the outer ring 1.
- the inner ring 3 is fixed by the holding element 7. Distributed over the circumference, for example, three such retaining elements 7 are provided.
- the Fig. 2 shows in simplified representation a view along the line AA-AA of Fig. 1 , As a result, it can be seen that the retaining element 7 is inserted into the groove 15 and is thus fixed radially, so that a reliable condition is ensured during operation of the gas turbine.
- the construction according to the invention has the advantage that when mounting the interstage seal arrangement or the gas turbine, the inner ring 3 can be mounted on the outer ring 1 in a simple manner. Subsequently, the holding elements 7 are then inserted and the guide vanes 2 inserted.
- the nose 28 on the inner ring 3 can be used in vertical mounting for holding the inner ring 3.
- Fig. 3 shows a modified embodiment in which a holding element 8 is formed as a pin-shaped extension of the strip 11, which passes through the recess 14 and thus directly secures the inner ring 3 against displacement forward when the vane 2 is mounted. From the representation of Fig. 3 Thus, it follows that the several retaining elements 8 uniformly distributed around the circumference are part of the strip 11 (guide blade rail) and thus serve simultaneously as axial retaining elements for both the outer ring and the inner ring.
- the respective holding element 9 is formed in the form of a pin which is pressed into a radial bore of the strip 11.
- FIGS. 5 and 6 show by way of example a further modification variant of the solution according to the invention.
- the same parts are again provided with the same reference numerals.
- the inner 3 and outer 1 ring are brought into the illustrated position.
- At least 3 holding elements 22 are now introduced from the outside into radial bores of the outer ring 1, wherein an inner part 26 of the holding element 22 engages in a groove of the inner ring 3.
- all holding elements 22 are finally pressed into their stop in the outer ring 1, wherein a central part 25 of the holding member 22 and the corresponding bore in the outer ring 1 are designed as a press fit.
- both rings 1, 3 are secured against each other and centered.
- An outer part 23 of at least 3 holding elements 22 finally engages in radial grooves 27 of the guide blade 11, whereby the centering of the outer ring 1 and thus the entire assembly is ensured by the guide vanes 2.
- recesses 24 are provided on the holding element, to which a removal tool can be attached.
- a significant advantage results according to the invention in that the choice of material for the outer ring and for the inner ring can be optimized separately and thus, for example, an optimal splitting behavior for the inner ring, while the outer ring, a high temperature resistant material can be selected.
- Another advantage may result in a weight saving as well as a reduction of the components and an associated reduction of the assembly costs.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung bezieht sich auf eine Zwischenstufendichtungsanordnung einer Gasturbine und im Speziellen auf eine Gasturbine mit einer schraubenlosen Zwischenstufendichtungs-Konstruktion.The invention relates to an interstage seal arrangement of a gas turbine, and more particularly to a gas turbine having a screwless interstage seal construction.
Bei Turbinenstufen von Gasturbinen ist es bekannt, die Rotorscheiben miteinander zu verschrauben. Dies erfolgt während der Montage so, dass die zwischen benachbarten Rotorscheiben angeordneten Zwischenstufendichtung bereits vormontiert sind. Diese sind so zu gestalten, dass die Zugänglichkeit zu den Scheibenflanschen der Rotorscheiben für deren Verschraubung gewährleistet und andererseits die Dichtfunktion erfüllt wird.In turbine stages of gas turbines, it is known to screw the rotor disks together. This takes place during assembly so that the arranged between adjacent rotor disks intermediate stage seal are already pre-assembled. These are to be designed so that the accessibility to the disc flanges of the rotor discs ensures their screwing and on the other hand, the sealing function is met.
Der Stand der Technik zeigt Konstruktionen, bei welchen die Zwischenstufendichtungsanordnung aus zwei Ringen besteht, die entweder einzeln, unabhängig voneinander an den Leitschaufeln befestigt werden oder die miteinander verschraubt werden. Eine weitere bekannte Ausführung ist die Teilung in zwei Halbringe, die erst nach der Verschraubung der Rotorscheiben montiert werden müssen.The prior art shows constructions in which the interstage seal assembly consists of two rings which are either individually secured to the vanes independently of each other or which are bolted together. Another known embodiment is the division into two half-rings, which must be mounted after screwing the rotor disks.
Bei den bekannten Ausgestaltungen mit verschraubten Ringen erweist es sich als nachteilig, dass die Verschraubung der Zwischenstufendichtungs-Teile hohen Temperaturen ausgesetzt ist. Bei einem Versagen der Verschraubung (Bruch einzelner Schrauben) ergeben sich Schäden an den Rotorscheiben. Weiterhin bringt die Verschraubung die Gefahr mit sich, dass andere Komponenten während des Montagevorgangs beschädigt werden können, beispielsweise eine Tannenbaumverzahnung an der Scheibe. Weiterhin erzeugt die Verschraubung eine Verwirbelung der Luftströme zwischen Rotor und Stator und erzeugt damit einen Luftwiderstand, der der Rotation entgegenwirkt. Die Verwirbelung führt auch zu einer Erhöhung der Lufttemperatur, die sich negativ auf die Scheibentemperatur sowie die Kühllufttemperatur für die nachfolgende Laufschaufel auswirkt. Ein weiterer, wesentlicher Nachteil besteht darin, dass die Werkstoffwahl für die Ringe der Zwischenstufendichtungsanordnung eingeschränkt ist, da die relative radiale Verschiebung aufgrund unterschiedlicher thermischer Dehnungen auf ein Minimum reduziert werden müssen, um ein Rutschen des Flansches und die damit verbundene Biegebelastung der Schrauben auszuschließen.In the known embodiments with screwed rings, it proves to be disadvantageous that the screw connection of the interstage seal parts is exposed to high temperatures. In case of failure of the screw (breakage of individual screws) results in damage to the rotor discs. Furthermore, the screwing involves the risk that other components may be damaged during the assembly process, for example, a Christmas tree toothing on the disc. Furthermore, the screw creates a turbulence of the air flows between the rotor and stator and thus generates an air resistance, which counteracts the rotation. The turbulence also leads to an increase in the air temperature, which has a negative effect on the disk temperature and the cooling air temperature for the subsequent blade. Another major drawback is that the material choice for the rings of the interstage seal assembly is limited since the relative radial displacement due to differential thermal expansion is minimized must be reduced in order to prevent slippage of the flange and the associated bending load of the screws.
Bei den aus dem Stand der Technik bekannten Lösungen mit zwei separaten Zwischenstufendichtungsringen handelt es sich um ein statisch unbestimmtes System, wobei durch Bauteiltoleranzen Zwangskräfte zwischen dem vorderen Ring und dem hinteren Ring (in Durchströmungsrichtung der Gasturbine gesehen) auftreten können. Bei einem der Ringe ist in der Regel der Druckunterschied der ihn umgebenden Luft so gering, dass keine oder nur geringe axiale Kräfte wirken. Dies kann zu Vibrationen und zu erhöhtem Verschleiß führen. Die in der Herstellung sehr kostenintensive Leitschaufel erfordert einen erhöhten Bearbeitungsaufwand. Weiterhin sind zusätzliche Dichtungsstreifen oder Dichtungselemente zwischen den Leitschaufelsegmenten erforderlich. Der Ring, der die Zwischenstufendichtung trägt, ist bei dieser Konstruktion zusätzlich einem hohen radialen Temperaturgradienten ausgesetzt.In the known from the prior art solutions with two separate interstage seal rings is a statically indeterminate system, which can occur by component tolerances constraining forces between the front ring and the rear ring (seen in the direction of flow of the gas turbine). In one of the rings is usually the pressure difference of the surrounding air so low that no or only small axial forces act. This can lead to vibrations and increased wear. The production of very costly vane requires increased processing costs. Furthermore, additional sealing strips or sealing elements are required between the vane segments. The ring carrying the interstage seal is also exposed to a high radial temperature gradient in this design.
Bei geteilten Zwischenstufendichtungsringen ist ein erhöhter Aufwand an Bearbeitung erforderlich. Insbesondere sind aufwändige Fräsarbeiten nötig. Eine derartige Baugruppe ist hinsichtlich ihrer Elemente aufeinander abgestimmt, so dass einzelne Elemente (beispielsweise Halbringe) nicht einzeln ausgetauscht werden können. Weiterhin ist eine derartige, systembedingt nicht rotationssymmetrische Konstruktion im Betrieb unsymmetrischen Thermaldehnungen ausgesetzt, so dass derartige Bauteile sich von einer kreisrunden Form in eine Ovalform verformen können. Hierdurch kann ein erhöhter Kaltspalt erforderlich sein und sich damit eine erhöhte Leckage ergeben.In split interstage seal rings an increased amount of processing is required. In particular, elaborate milling work is necessary. Such an assembly is matched with respect to their elements, so that individual elements (for example, half-rings) can not be replaced individually. Furthermore, such a system-inherently non-rotationally symmetrical construction is exposed during operation to asymmetrical thermal expansions, so that such components can deform from a circular shape into an oval shape. As a result, an increased cold gap may be required and thus result in increased leakage.
Der Erfindung liegt die Aufgabe zugrunde, eine Zwischenstufendichtungsanordnung einer Gasturbine der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit die Nachteile des Standes der Technik vermeidet und insbesondere gute konstruktive Eigenschaften aufweist.The invention has for its object to provide an intermediate stage seal arrangement of a gas turbine of the type mentioned, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and in particular has good structural properties.
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 Zwischenstufendichtungsanordnung einen (radial) äußeren Ring, welcher durch Leitschaufeln sowohl axial gehalten, als auch zentriert und somit gelagert wird, sowie einen (radial) inneren Ring, welcher an dem äußeren Ring gelagert ist, umfasst. Die Begriffe (radial) äußerer und (radial) innerer beziehen sich auf die Rotationsachse oder Maschinenachse. Mit den Begriffen vordere und hintere wird auf die Durchströmungsrichtung der Gasturbine Bezug genommen, vordere bedeutet somit näher am Einlaufbereich, während hintere näher am Auslassbereich bedeutet.According to the invention, it is thus provided that the interstage seal arrangement has a (radially) outer ring, which is held both axially by guide vanes Also centered and thus stored, and a (radial) inner ring which is mounted on the outer ring comprises. The terms (radially) outer and (radial) inner refer to the axis of rotation or machine axis. With the terms front and rear reference is made to the direction of flow of the gas turbine, front thus means closer to the inlet region, while rear means closer to the outlet.
Erfindungsgemäß ist jeder der Ringe, nämlich der äußere Ring und der innere Ring, mit zumindest einem Dichtungsbereich versehen, um die Funktion einer Zwischenstufendichtungsanordnung zu erfüllen.According to the invention, each of the rings, namely the outer ring and the inner ring, is provided with at least one sealing area to perform the function of an interstage seal arrangement.
Weiterhin ist erfindungsgemäß vorgesehen, dass der innere Ring am äußeren Ring durch mindestens drei radiale Nut-Feder-Verbindungen, im folgenden Radialnutenzentrierung genannt, zentriert und auch gegen Verdrehen in Umfangsrichtung gesichert ist. Die Symmetrieebenen aller Nut-Feder-Verbindungen müssen alle die Hauptrotationsachse der beteiligten Komponenten enthalten, um eine Verformung oder Beschädigung zu verhindern. Dieses Prinzip entspricht dem Stand der Technik und wird u.a. auch für die Zentrierung des äußeren Ringes durch die Leitschaufeln verwendet. Es erlaubt unterschiedliche thermische Expansionen der beteiligten Komponenten bei gleichzeitiger Sicherstellung der Koaxialität.Furthermore, the invention provides that the inner ring on the outer ring by at least three radial tongue and groove connections, referred to below Radialnutenzentrierung centered and is secured against rotation in the circumferential direction. The planes of symmetry of all tongue and groove joints must all contain the main axis of rotation of the components involved to prevent deformation or damage. This principle corresponds to the state of the art and is u.a. also used for the centering of the outer ring by the vanes. It allows different thermal expansions of the components involved while ensuring coaxiality.
Bezüglich der axialen Fixierung des äußeren Ringes durch in dessen Umfangsnut (nach außen offene Nut) eingreifende Leisten der Leitschaufeln kann auf den Stand der Technik verwiesen werden. Der innere Ring wird hingegen durch einen ringförmigen Ansatz des äußeren Ringes axial nach hinten gesichert. Das Anliegen des inneren Ringes am äußeren Ring wird im Betrieb durch das Druckgefälle zwischen der vorne liegenden, ersten Stufe und der hinter der Zwischenstufendichtungsanordnung befindlichen zweiten Stufe sichergestellt. Im Stillstand könnte sich der innere Ring nach vorne bewegen. Dies wird jedoch erfindungsgemäß mittels mehrerer Halteelemente verhindert. Erfindungsgemäß sind diese Halteelemente selbst von außen demontierbar, um ein Verschieben des inneren Ringes nach vorne bzw. des äußeren Ringes nach hinten zum Verschrauben der Rotorscheiben zu ermöglichen. Erfindungsgemäß werden die Halteelemente selbst durch die Leisten der Leitschaufeln gegen Herausfallen gesichert.With respect to the axial fixation of the outer ring by engaging in the circumferential groove (outwardly open groove) strips of the guide vanes may be made to the prior art. The inner ring, however, is secured axially to the rear by an annular projection of the outer ring. The engagement of the inner ring on the outer ring is ensured in operation by the pressure differential between the front, first stage and located behind the interstage seal assembly second stage. At a standstill, the inner ring could move forward. However, this is prevented according to the invention by means of a plurality of holding elements. According to the invention, these holding elements can be disassembled even from the outside in order to enable a displacement of the inner ring to the front or of the outer ring to the rear for screwing the rotor disks. According to the invention, the holding elements are themselves secured against falling out by the strips of the guide vanes.
Die Umfangsnut im äußeren Ring kann zum Einlegen von Halteelementen ausgebildet sein. Hierdurch ist die Umfangsnut entweder am gesamten Umfangsbereich oder über einen Teil ihres Umfangs mit einer größeren axialen Breite versehen, die es gestattet, neben der Leiste der Leitschaufel zusätzlich Halteelemente einzubringen. Am Umfang sind beispielsweise drei derartige Halteelemente vorgesehen, die ausreichend sind, um im Stillstand des Triebwerks den inneren Ring gegen ein axiales Verrutschen zu sichern.The circumferential groove in the outer ring can be designed for inserting retaining elements. As a result, the circumferential groove is provided either over the entire peripheral region or over part of its circumference with a larger axial width, which makes it possible to introduce additional holding elements in addition to the strip of the guide vane. At the periphery, for example, three such holding elements are provided which are sufficient to secure the inner ring against axial slipping when the engine is at a standstill.
Zur Erhöhung der Dichtwirkung zwischen dem äußeren Ring und dem inneren Ring kann es günstig sein, wenn der äußere Ring und/oder der innere Ring an dem jeweiligen Anlagebereich mit einem ringwulstförmigen Dichtungsvorsprung versehen ist.To increase the sealing effect between the outer ring and the inner ring, it may be advantageous if the outer ring and / or the inner ring is provided at the respective contact area with a ring bead-shaped sealing projection.
In einer alternativen Ausgestaltung der Erfindung ist es auch möglich, nach innen weisende Halteelemente vorzusehen, welche an der Leiste der Leitschaufel selbst ausgebildet sind, entweder als Stifte, die in radiale Bohrungen der Leiste eingepresst sind, oder als Verlängerungen von Teilbereichen der Leiste in radialer Richtung.In an alternative embodiment of the invention, it is also possible to provide inwardly facing retaining elements which are formed on the strip of the vane itself, either as pins which are pressed into radial bores of the strip, or as extensions of portions of the strip in the radial direction ,
Erfindungsgemäß ist weiterhin in bevorzugter Ausgestaltung der Erfindung vorgesehen, dass Halteelemente in radiale Bohrungen des äußeren Ringes eingepresst werden und diese stiftartigen Halteelemente die Rückhaltefunktion für den inneren Ring übernehmen. Die stiftartigen Halteelemente können dabei so gestaltet werden, dass sie sowohl die Zentrierung zwischen Leitschaufeln und äußeren Ring sowie zwischen äußeren und inneren Ring sicherstellen.According to the invention is further provided in a preferred embodiment of the invention that retaining elements are pressed into radial holes of the outer ring and these pin-like holding elements take over the retention function for the inner ring. The pin-like holding elements can be designed so that they ensure both the centering between guide vanes and outer ring and between the outer and inner ring.
Erfindungsgemäß ist es somit möglich, gleichzeitig, über den Umfang verteilt, mehrere der stiftartigen Halteelemente (Rückhalteelemente) vorzusehen, die gleichzeitig als Zentrierelemente sowohl für den äußeren als auch für den inneren Ring dienen und eine Axialsicherungsfunktion übernehmen. Durch die Übernahme der Zentrierfunktion durch die Halteelemente können die im Stand der Technik vorgesehenen zusätzlichen Radialnutenzentrierungen entfallen. Hierdurch ergibt sich eine einfachere Konstruktion, welche sowohl in niedrigeren Kosten als auch in niedrigerem Gewicht resultiert. Aufgrund der Presspassung der Halteelemente mit dem äußeren Ring wird weiterhin das Auftreten von Leckagen vermindert oder gänzlich eliminiert.According to the invention, it is thus possible, at the same time, distributed over the circumference, to provide a plurality of the pin-like holding elements (retaining elements) which simultaneously serve as centering elements for both the outer ring and the inner ring and assume an axial securing function. By assuming the centering function by the holding elements provided in the prior art additional Radialnutenzentrierungen can be omitted. This results in a simpler construction, which results in both lower costs and lower weight. Due to the interference fit of the retaining elements with the outer ring, the occurrence of leakage is further reduced or eliminated altogether.
Die Einbringung der radialen Bohrungen im äußeren Ring ist erfindungsgemäß einfach möglich, insbesondere sind dabei keine weiteren Modifikationen an den Leitschaufeln bzw. den Füßen der Leitschaufeln erforderlich. Auch hierdurch ergibt sich eine nicht unerhebliche Kostenersparnis.The introduction of the radial bores in the outer ring according to the invention is easily possible, in particular, no further modifications to the guide vanes or the feet of the vanes are required. This also results in a significant cost savings.
Erfindungsgemäß ist es somit in besonders günstiger Weise möglich, den äußeren Ring und den inneren Ring aus unterschiedlichen Materialien zu fertigen, so dass der äußere Ring und der innere Ring hinsichtlich ihrer thermischen Beanspruchungen optimiert werden können.According to the invention it is thus possible in a particularly favorable manner, to manufacture the outer ring and the inner ring of different materials, so that the outer ring and the inner ring can be optimized in terms of their thermal stresses.
Alle Varianten der erfindungsgemäßen Lösung adressieren bzw. eliminieren die Nachteile der aus dem Stand der Technik bekannten Konstruktionen, im Einzelnen:
- Eliminierung des Fehlerfalles "Versagen der Verschraubung";
- Geringere Strömungsverluste durch Wegfall der Verschraubung;
- Werkstoffe können unabhängig für eine optimale Funktion gewählt werden, z.B. optimales Spaltverhalten für den inneren Ring und hochtemperaturbeständiger Werkstoff für den äußeren Ring.
- Elimination of the error case "Failure of the screw connection";
- Lower flow losses due to elimination of the screw connection;
- Materials can be independently selected for optimum performance, eg optimal splitting behavior for the inner ring and high temperature resistant material for the outer ring.
Im Folgenden wird die Erfindung anhand von Ausführungsbeispielen in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:
- Fig. 1
- eine axiale Teil-Schnittansicht einer erfindungsgemäßen Zwischenstufendichtungsanordnung gemäß einem ersten Ausführungsbeispiel,
- Fig. 2
- eine vereinfachte Teil-Ansicht längs der Schnittlinie AA-AA gemäß
Fig. 1 , - Fig. 3
- eine Ansicht eines abgewandelten Ausführungsbeispiels, analog
Fig. 1 , - Fig. 4
- eine Ansicht, analog
Fig. 1 , eines weiteren Ausführungsbeispiels, - Fig. 5
- eine weitere Ausführungsvariante gemäß der Erfindung in vergrößerter Schnittansicht analog den
Fig. 1 bis 4 , und - Fig. 6
- eine Schnittansicht längs der Linie AB gemäß
Fig. 5 .
- Fig. 1
- FIG. 2 is a partial axial sectional view of an interstage seal assembly according to a first embodiment of the present invention; FIG.
- Fig. 2
- a simplified partial view along the section line AA-AA according to
Fig. 1 . - Fig. 3
- a view of a modified embodiment, analog
Fig. 1 . - Fig. 4
- a view, analog
Fig. 1 , another embodiment, - Fig. 5
- a further embodiment according to the invention in an enlarged sectional view analogous to
Fig. 1 to 4 , and - Fig. 6
- a sectional view taken along the line AB according to
Fig. 5 ,
Bei den Ausführungsbeispielen sind gleiche Teile jeweils mit gleichen Bezugsziffern versehen. Aus Übersichtlichkeitsgründen wird bei den
Die
Der äußere Ring 1 umfasst eine sich in Umfangsrichtung erstreckende, radial nach außen offene Nut 12, in welche eine radial nach innen weisende Leiste 11 eines Fußes einer Leitschaufel 2 eingesteckt ist. Die Leitschaufeln 2 sind gemäß dem Stand der Technik ausgebildet und in Umfangsrichtung segmentiert, wobei jeweils auch mehrere Leitschaufeln 2 einen gemeinsamen Fuß 16 aufweisen können.The
Die
Bei dem in
Radial innen zu dem äußeren Ring 1 ist der innere Ring 3 angeordnet. Dieser liegt gegen einen ringförmigen Ansatz 10 des äußeren Rings 1 an und wird somit in Axialrichtung abgestützt. Der ringförmige Ansatz 10 bildet somit einen Anlageschenkel und fixiert den inneren Ring 3, wobei der innere Ring 3 an seiner radialen Außenseite mit einem Freiraum zur thermischen Expansion gegenüber dem äußeren Ring 1 versehen ist. Auf der dem ringförmigen Ansatz 10 gegenüberliegenden Seite wird der innere Ring 3 durch das Halteelement 7 fixiert. Über den Umfang verteilt sind beispielsweise drei derartige Halteelemente 7 vorgesehen.Radially inward to the
Die
Die erfindungsgemäße Konstruktion weist den Vorteil auf, dass bei einer Montage der Zwischenstufendichtungsanordnung bzw. der Gasturbine der innere Ring 3 an dem äußeren Ring 1 in einfacher Weise montiert werden kann. Nachfolgend werden dann die Halteelemente 7 eingesetzt und die Leitschaufeln 2 eingesteckt.The construction according to the invention has the advantage that when mounting the interstage seal arrangement or the gas turbine, the
Die Nase 28 am inneren Ring 3 kann bei senkrechter Montage zum Halten des inneren Rings 3 verwendet werden.The
Die
Bei dem in
Die
Nach der Verschraubung des Rotors werden der innere 3 und äußere 1 Ring in die abgebildete Position gebracht. Mindestens 3 Halteelemente 22 werden nun von außen in radiale Bohrungen des äußeren Ringes 1 eingeführt, wobei ein innerer Teil 26 des Halteelementes 22 in eine Nut des inneren Ringes 3 eingreift. Nun werden alle Halteelemente 22 endgültig bis zu ihrem Anschlag in den äußeren Ring 1 gedrückt, wobei ein mittlerer Teil 25 des Halteelements 22 und die entsprechende Bohrung im äußeren Ring 1 als Presspassung ausgelegt sind. Hiermit sind beide Ringe 1, 3 gegeneinander gesichert und zentriert. Ein äußerer Teil 23 von mindestens 3 Halteelementen 22 greift schließlich in radiale Nuten 27 der Leitschaufelleiste 11 ein, wodurch auch die Zentrierung des äußeren Ringes 1 und somit der gesamten Baugruppe durch die Leitschaufeln 2 sichergestellt wird.After screwing the rotor, the inner 3 and outer 1 ring are brought into the illustrated position. At least 3 holding
Zur Demontage sind am Halteelement 22 Ausnehmungen 24 vorgesehen, an denen ein Abziehwerkzeug angesetzt werden kann.For
Erfindungsgemäß ergibt sich somit der Vorteil, dass ein Versagen von Verschraubungen ausgeschlossen werden kann, da keine Verschraubungen zwischen dem äußeren Ring und dem inneren Ring vorgesehen sind. Hierdurch ergeben sich auch geringere Strömungsverluste, da die Oberflächen des äußeren Rings und des inneren Rings jeweils strömungsgünstig optimiert werden können.According to the invention thus results in the advantage that a failure of glands can be excluded because no glands between the outer ring and the inner ring are provided. This also results in lower flow losses, since the surfaces of the outer ring and the inner ring can each be streamlined optimized.
Ein wesentlicher Vorteil ergibt sich erfindungsgemäß darin, dass die Werkstoffauswahl für den äußeren Ring und für den inneren Ring getrennt optimierbar sind und somit beispielsweise ein optimales Spaltverhalten für den inneren Ring ermöglichen, während bei dem äußeren Ring ein hochtemperaturbeständiger Werkstoff gewählt werden kann.A significant advantage results according to the invention in that the choice of material for the outer ring and for the inner ring can be optimized separately and thus, for example, an optimal splitting behavior for the inner ring, while the outer ring, a high temperature resistant material can be selected.
Ein weiterer Vorteil kann in einer Gewichtseinsparung sowie einer Reduzierung der Bauteile und einer damit verbundenen Reduzierung der Montagekosten resultieren.Another advantage may result in a weight saving as well as a reduction of the components and an associated reduction of the assembly costs.
- 11
- Äußerer Ring-Outer ring
- 22
- Leitschaufel-Vane-
- 33
- Innerer RingInner ring
- 44
- Dichtungsbereichsealing area
- 55
- Dichtungsbereichsealing area
- 66
- Dichtungsbereichsealing area
- 77
- Halteelementretaining element
- 88th
- Halteelementretaining element
- 99
- Halteelementretaining element
- 1010
- Ringförmiger AnsatzRing-shaped approach
- 1111
- Leistestrip
- 1212
- Umfangsnut / NutCircumferential groove / groove
- 1313
- Dichtungsvorsprungsealing projection
- 1414
- Ausnehmungrecess
- 1515
- Nutgroove
- 1616
- Fußfoot
- 1717
-
Scheibe der Stufe 1
Level 1 disk - 1818
-
Scheibe der Stufe 2
Level 2 disk - 1919
- Rotorschaufelrotor blade
- 2020
- Rotorschaufelrotor blade
- 2121
- Fußfoot
- 2222
- Halteelementretaining element
- 2323
- äußerer Teilouter part
- 2424
- Ausnehmungrecess
- 2525
- mittlerer Teilmiddle part
- 2626
- innerer Teilinner part
- 2727
- radiale Nutradial groove
- 2828
- Nasenose
Claims (13)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE201010007724 DE102010007724A1 (en) | 2010-02-12 | 2010-02-12 | Screwless intermediate stage seal of a gas turbine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2360352A2 true EP2360352A2 (en) | 2011-08-24 |
EP2360352A3 EP2360352A3 (en) | 2017-08-09 |
EP2360352B1 EP2360352B1 (en) | 2018-08-08 |
Family
ID=43708799
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11001144.2A Active EP2360352B1 (en) | 2010-02-12 | 2011-02-11 | Screw-free intermediate stage seal of a gas turbine |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2360352B1 (en) |
DE (1) | DE102010007724A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2650482A1 (en) * | 2012-01-20 | 2013-10-16 | General Electric Company | Near Flow Path Seal with Axially Flexible Arms |
EP2696039A1 (en) * | 2012-08-10 | 2014-02-12 | MTU Aero Engines GmbH | Gas turbine stage |
GB2540233A (en) * | 2015-03-02 | 2017-01-11 | Rolls Royce Plc | Seal arrangement |
EP3517734A1 (en) * | 2018-01-29 | 2019-07-31 | MTU Aero Engines GmbH | Sealing module for a turbomachine |
EP3885536A1 (en) * | 2020-03-25 | 2021-09-29 | MTU Aero Engines AG | Gas turbine component |
CN116399526A (en) * | 2023-06-05 | 2023-07-07 | 中国航发四川燃气涡轮研究院 | Circumferential sealing effect verification device for guide vane of aero-engine |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012014109A1 (en) | 2012-07-17 | 2014-01-23 | Rolls-Royce Deutschland Ltd & Co Kg | Washer seal for use in gas turbine engine, has sealing ring, which is arranged between radially outer sections of rotor disks and is clamped between rotor disks in axial direction, where sealing elements are arranged on sealing ring |
FR3106626B1 (en) * | 2020-01-24 | 2022-06-10 | Safran Aircraft Engines | DIFFERENTIATED SWITCHING BETWEEN ROTOR AND STATOR AT ROTOR-STATOR AIR GATES IN A TURBOMACHINE COMPRESSOR |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
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FR957575A (en) * | 1946-10-02 | 1950-02-23 | ||
US5224822A (en) * | 1991-05-13 | 1993-07-06 | General Electric Company | Integral turbine nozzle support and discourager seal |
DE19931765A1 (en) * | 1999-07-08 | 2001-01-11 | Rolls Royce Deutschland | Two/multistage axial turbine esp. for aircraft gas turbine has intermediate stage sealing ring with ring elements held together by piston ring-type securing ring |
DE10214624C1 (en) * | 2001-10-29 | 2003-03-27 | Man Turbomasch Ag Ghh Borsig | Seal device for turbomachine has heat elastic inner ring fitted to blade foot provided with cooled dovetail seal cooperating with rotor labyrinth |
JP3911571B2 (en) * | 2002-05-21 | 2007-05-09 | 川崎重工業株式会社 | Gas turbine sealing method and sealing structure |
GB0424883D0 (en) * | 2004-11-11 | 2004-12-15 | Rolls Royce Plc | Seal structure |
FR2908153B1 (en) * | 2006-11-07 | 2011-05-13 | Snecma | DEVICE FOR HITCHING A DISTRIBUTOR (8) OF A TURBINE, TURBINE COMPRISING THEM, AND AN AIRCRAFT ENGINE WHICH IS EQUIPPED |
-
2010
- 2010-02-12 DE DE201010007724 patent/DE102010007724A1/en not_active Withdrawn
-
2011
- 2011-02-11 EP EP11001144.2A patent/EP2360352B1/en active Active
Non-Patent Citations (1)
Title |
---|
None |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2650482A1 (en) * | 2012-01-20 | 2013-10-16 | General Electric Company | Near Flow Path Seal with Axially Flexible Arms |
US9080456B2 (en) | 2012-01-20 | 2015-07-14 | General Electric Company | Near flow path seal with axially flexible arms |
EP2696039A1 (en) * | 2012-08-10 | 2014-02-12 | MTU Aero Engines GmbH | Gas turbine stage |
GB2540233A (en) * | 2015-03-02 | 2017-01-11 | Rolls Royce Plc | Seal arrangement |
EP3517734A1 (en) * | 2018-01-29 | 2019-07-31 | MTU Aero Engines GmbH | Sealing module for a turbomachine |
US20190234225A1 (en) * | 2018-01-29 | 2019-08-01 | MTU Aero Engines AG | Module for a turbomachine |
US10844737B2 (en) * | 2018-01-29 | 2020-11-24 | MTU Aero Engines AG | Additively manufactured module for a turbomachine |
EP3885536A1 (en) * | 2020-03-25 | 2021-09-29 | MTU Aero Engines AG | Gas turbine component |
US11585242B2 (en) | 2020-03-25 | 2023-02-21 | MTU Aero Engines AG | Gas turbine component |
CN116399526A (en) * | 2023-06-05 | 2023-07-07 | 中国航发四川燃气涡轮研究院 | Circumferential sealing effect verification device for guide vane of aero-engine |
CN116399526B (en) * | 2023-06-05 | 2023-09-01 | 中国航发四川燃气涡轮研究院 | Circumferential sealing effect verification device for guide vane of aero-engine |
Also Published As
Publication number | Publication date |
---|---|
EP2360352A3 (en) | 2017-08-09 |
EP2360352B1 (en) | 2018-08-08 |
DE102010007724A1 (en) | 2011-08-18 |
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