EP2851518A1 - Component system of a turbo engine - Google Patents
Component system of a turbo engine Download PDFInfo
- Publication number
- EP2851518A1 EP2851518A1 EP14185872.0A EP14185872A EP2851518A1 EP 2851518 A1 EP2851518 A1 EP 2851518A1 EP 14185872 A EP14185872 A EP 14185872A EP 2851518 A1 EP2851518 A1 EP 2851518A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- component
- segment
- component segment
- overlapping
- elements
- 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
Links
- 238000007789 sealing Methods 0.000 claims abstract description 21
- 238000000034 method Methods 0.000 claims abstract description 8
- 230000000295 complement effect Effects 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000004026 adhesive bonding Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005476 soldering Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000005304 joining Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Images
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
- 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
- F01D11/005—Sealing means between non relatively rotating elements
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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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
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
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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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- the invention relates to a component system of a turbomachine, in particular an aircraft turbine.
- the invention further relates to a method for mounting such a component system and a turbomachine with such a component system.
- a component system of an aircraft turbine which comprises a plurality of component segments each formed as a shroud segments, which are arranged in a housing annularly around a rotor of the aircraft turbine.
- Each component segment includes two opposing abutment surfaces which, when assembled, abut an associated abutment surface of the respective adjoining component segment.
- sealing plates are inserted into grooves provided for the individual abutment surfaces for sealing the segmental joints.
- component segments with simple joints or abutment surfaces and seal the shocks by mounting a circumferential sealing plate on these component segments.
- component segments are used with permanently attached sealing plates, wherein the sealing plates rest on the respective adjacent component segment or are taken in grooves or brackets.
- the sealing effect is strongly influenced by the different tolerance chains, so that only a comparatively poor sealing of the segment joints can be achieved.
- the use of individual sealing sheets leads to a high assembly and disassembly effort and thus to correspondingly high manufacturing and repair costs.
- Object of the present invention is to provide a component system of the type mentioned, which allows an improved seal and beyond is simpler and less expensive to install.
- Another object of the invention is to provide a method of assembling such a component system as well as a turbomachine having such a component system.
- a first aspect of the invention relates to a component system which allows for improved sealing and moreover is simpler and more cost-effective to assemble, in that at least the first component segment and the second component segment for sealing a gap between the abutting surfaces together comprise at least three overlapping elements. It is further provided that each overlap element overlaps in abutting abutting surfaces with the respective other component segment in the radial direction, that at least two of the overlapping elements are formed on the first component segment, that at least one of the overlapping elements is formed on the second component segment and that the overlap element of the second component segment is arranged in abutting abutting surfaces in the axial direction between the overlapping elements of the first component segment.
- component segments which adjoin one another in the assembled state, each comprise overlapping elements which overlap in the assembled state with the respective other component segment.
- This segment seal is integrated into the component segments in such a way that at least three overlapping elements are provided per joint or abutting surface pair, at least two of the overlapping elements being attached to the first component segment, ie on the first bank, and at least one of the overlapping elements on the second component segment, that is is formed on the second bank and also between the two overlapping elements of the first component segment.
- the component system according to the invention has only two such component segments, which complement each other to form a ring.
- the component system three, four, five, six has seven, eight, nine, ten or more component segments, which are provided in the above manner with overlapping elements.
- all the component segments of the component system complement each other in the mounted state to form a ring whose center axis preferably runs coaxially to the axis of the rotor of the turbomachine.
- the alternate arrangement and coverage of the overlap elements has the advantage that the leakage gaps between the abutment surfaces of the component segments are determined at least substantially only by the component segments themselves, but not by other components.
- the tolerance chain for the individual leakage gaps can be greatly reduced in this way. Due to the alternating arrangement of the overlapping elements can also be achieved that the component elements fix each other and not need to be fixed by additional housing receptacles or the like. This allows a further reduction of the tolerance chain and thus an improved gap seal.
- At least one of the overlap elements is integrally formed on the relevant component segment and / or is connected by a material fit to the relevant component segment.
- the overlapping element concerned may be fastened to the relevant component segment by welding, soldering and / or gluing, for example.
- the two overlapping elements of the first component segment are formed on opposite outer regions of the first component segment and / or that the overlapping element of the second component segment is formed in the axially central region of the second component segment.
- the overlapping elements jointly at least abdicht the gap between the abutment surfaces in abutting abutting surfaces.
- the overlapping elements in the assembled state of the component segments together at least substantially cover the impact gap, whereby a particularly high sealing effect is achieved.
- the overlapping elements if they are mounted at different radial distances or planes, are arranged above or below each other at least in regions. In this way, a kind of labyrinth seal can be generated, whereby a particularly high sealing effect can be achieved.
- At least one of the overlapping elements is hook-shaped and / or rectangular in cross-section and / or trough-shaped and / or V-shaped and / or U-shaped.
- the overlapping elements are basically not limited in their shape, a hook-shaped configuration of at least one of the overlapping elements can be used to construct a kind of clip connection between the component segments in a structurally simple manner. After assembly, an undesired relative movement of adjacent component segments in the circumferential direction is thus avoided particularly reliably.
- at least one of the overlapping elements may be formed rectangular, V-shaped and / or U-shaped, which in addition to a falloptim convinced segment seal additionally increased mechanical stability and protection against unwanted relative movements of the component segments against each other can be ensured.
- a mechanically particularly stable connection of the component segments is made possible in a further embodiment of the invention in that the first component segment and / or the second Component segment comprises at least one overlap region which is complementary to the associated overlap element of the respective other component segment.
- the overlapping element of the second component segment has a larger surface area and / or a greater axial extent than the overlapping elements of the first component segment, a particularly good segmental sealing is achieved.
- first component segment and / or the second component segment is designed as a guide ring segment and / or as a turbine ring segment.
- advantages of the component system according to the invention for said turbine elements can be realized, in which a reliable sealing of the abutting surfaces between the individual component segments and a simple assembly and disassembly is of particularly high importance.
- a geometrically particularly exact production with simultaneously low production costs is achieved in a further embodiment of the invention in that at least one of the component segments is produced generatively. It can furthermore be provided that two, several or all component segments of the component system are or are produced generatively.
- a second aspect of the invention relates to a method for mounting a component system according to the first aspect of the invention in a turbomachine, in which at least the first component segment and the second component segment of the component system are joined such that the abutment surface of the first component segment and the abutment surface of the second component segment abut each other in that the at least two overlapping elements of the first component segment overlap in the radial direction with the second component segment, that the at least one overlapping element of the second component segment overlaps in the radial direction with the first component segment, and in that the overlapping element of the second component segment extends axially between the two overlap elements of the first component segment Component segment is arranged.
- the at least two component segments are pushed toward one another, so that the overlapping elements come to lie alternately on the respective other component segment in the aforementioned manner.
- the component system can basically be mounted inside a housing of the turbomachinery or outside be mounted and then mounted in the composite in the housing or installed.
- a disassembly for example for maintenance, repair or overhaul purposes can accordingly be made in the reverse order or by pulling the component segments in the circumferential direction.
- a third aspect of the invention relates to a turbomachine, in particular an aircraft engine, which comprises a component system which is designed according to the first aspect of the invention and / or is mounted by means of a method according to the second aspect of the invention.
- Fig. 1 shows a schematic perspective view of a component system 10 according to a first embodiment of the invention.
- the component system 10 comprises a plurality of component segments, of which only a first component segment 12a and a second component segment 12b are shown in fragmentary form.
- the component system 10 is designed as a guide vane of an aircraft turbine (not shown) and comprises further component segments, not shown, which are formed analogously to the component segments 12a, 12b shown and complement each other to form a ring.
- the component segments are arranged for mounting annularly about an axis of a rotor of the aircraft engine, so that in each case an abutment surface 14a of the first component segment 12a and an abutment surface 14b of the second component segment 12b abut each other.
- the abutment surfaces 14a, 14b are respectively provided on the narrow sides of the component segments 12a, 12b.
- the opposing abutment surfaces of the individual component segments 12a, 12b which are not shown, can in principle be identical or complementary to the abutment surfaces 14a, 14b, in order to ensure a mutually secure assembly of all component segments. For assembly all component segments are pushed towards each other in the circumferential direction until their respective abutment surfaces abut each other or abut each other.
- the component segments 12a, 12b have a total of three overlap elements 16a-c for each abutment surface pairing. It can be seen that the overlapping elements 16a-c in the abutting abutting surfaces 14a, 14b overlap with the respective other component segment 12a, 12b in the radial direction, so that the component segments 12a, 12b only in the circumferential direction, but not in the axial or radial direction relative to each other can be moved.
- the overlapping element 16a according to arrow Ia is on the associated, complementarily formed overlap region 18a to lie
- the overlap element 16b comes to lie according to arrow Ib on the associated, complementarily formed overlap region 18b
- the overlap element 16c comes according to arrow Ic on the associated, complementary formed Overlap area 18c to lie.
- all the overlapping elements 16a-c are integrally formed with the respective component segment 12a, 12b. This can be achieved in a particularly simple and cost-effective manner, for example by generative production of the component segments 12a, 12b. Furthermore, it is off Fig.
- the individual overlap element 16b formed in the middle of the second component segment 12b and accordingly in the assembled state between the respective outer overlap elements 16a, 16c of the first component segment 12b is arranged.
- the second, opposing overlap element 16b has a larger surface area and a greater axial extent than the outer overlap elements 16a, 16c of the first component segment 12a, is formed in another radially outermost plane than the overlap elements 16a, 16c, and a has different geometry than the overlap elements 16a, 16c.
- the overlapping elements 16a, 16c are cuboid or rectangular in cross-section, while the overlapping element 16b is formed in a trough-shaped or approximately V-shaped cross-section.
- the segment seal is integrated into the component segments 12a, 12b in such a way that at least three overlap elements 16a-c are provided per joint surface pair, of which two overlap elements 16a, 16c are mounted on the first bank (component segment 12a), while the further overlap element 16b is mounted on the second bank (component segment 12b) and between the two other overlap elements 16a, 16c, so that in the mounted state an alternately overlap results.
- the leakage gaps are determined only by the component segments themselves, since they are fixed to each other and need not be fixed by housing receivers or the like.
- the tolerance chain for the leakage gap can thus be reduced.
- no loose or separate parts are required for the seal. It may in principle be provided that the first component segment 12a and / or the second component segment 12b have one or more further overlap elements.
- Fig. 2 shows a partially transparent schematic perspective view of the component system 10 according to a second embodiment of the invention.
- the component system 10 also includes a plurality of component segments, of which only a first component segment 12a and a second component segment 12b are shown in fragmentary form. It can be seen that the component segments 12a, 12b, the first, in the present case V-shaped overlapping element 16a and the second overlapping element 16b have different geometries compared to the preceding embodiment, while the overlapping element 16c is also rectangular in cross-section or rectangular in cross-section.
- the overlap elements 16a and 16c not integrally formed, but materially connected, for example by welding, soldering or gluing, with the component segment 12a.
- the second overlapping element 16b can be connected to the component segment 12b by material engagement, for example by welding, soldering or gluing.
- the component segments 12a, 12b at their radial inner sides sealing elements 20a, 20b which may be formed, for example, as honeycomb seals for turbine blades.
- the basic principle of the component system 10 with the alternate overlapping of the overlapping elements 16a-c corresponds to that of the preceding embodiment, so that during assembly or during joining of the component segments 12a, 12b according to the arrows IIa-c, a corresponding overlap and segment sealing occurs.
- deviating geometries of the overlapping elements 16a-c are also conceivable in principle.
- at least one of the overlapping elements 16a-c may be hook-shaped, so that the component segments 12a, 12b latch when pushed together in the manner of a clip connection and are fixed relative to one another.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Die Erfindung betrifft ein Bauteilsystem (10) einer Turbomaschine, insbesondere einer Flugzeugturbine, umfassend wenigstens ein erstes Bauteilsegment (12a) und ein zweites Bauteilsegment (12b), die ringsegmentförmig um eine Achse eines Rotors der Turbomaschine anordenbar sind, so dass zumindest eine Stoßfläche (14a) des ersten Bauteilsegments (12a) und eine Stoßfläche (14b) des zweiten Bauteilsegments (12b) aufeinander stoßen, wobei das erste Bauteilsegment (12a) und das zweite Bauteilsegment (12b) zur Abdichtung eines Spalts zwischen den Stoßflächen (14a, 14b) zusammen mindestens drei Überlappungselemente (16a-c) umfassen. Jedes Überlappungselement (16a-c) überlappt bei aufeinander stoßenden Stoßflächen (14a, 14b) mit dem jeweils anderen Bauteilsegment (12a, 12b) in radialer Richtung. Wenigstens zwei der Überlappungselemente (16a, 16c) sind am ersten Bauteilsegment (12a) ausgebildet, während wenigstens eines der Überlappungselemente (16b) am zweiten Bauteilsegment (12b) ausgebildet ist. Das Überlappungselement (16b) des zweiten Bauteilsegments (12b) ist bei aufeinander stoßenden Stoßflächen (14a, 14b) in axialer Richtung zwischen den Überlappungselementen (16a, 16c) des ersten Bauteilsegments (12a) angeordnet. Die Erfindung betrifft weiterhin ein Verfahren zum Montieren eines solchen Bauteilsystems (10) sowie eine Turbomaschine mit einem derartigen Bauteilsystem (10).The invention relates to a component system (10) of a turbomachine, in particular an aircraft turbine, comprising at least a first component segment (12a) and a second component segment (12b) which can be arranged in the form of a ring segment about an axis of a rotor of the turbomachine, such that at least one abutment surface (14a ) of the first component segment (12a) and an abutment surface (14b) of the second component segment (12b), wherein the first component segment (12a) and the second component segment (12b) for sealing a gap between the abutment surfaces (14a, 14b) together at least three overlap elements (16a-c). Each overlapping element (16a-c) overlaps with the abutting abutting surfaces (14a, 14b) with the respective other component segment (12a, 12b) in the radial direction. At least two of the overlap elements (16a, 16c) are formed on the first component segment (12a), while at least one of the overlap elements (16b) is formed on the second component segment (12b). The overlapping element (16b) of the second component segment (12b) is arranged in the axial direction between the overlapping elements (16a, 16c) of the first component segment (12a) in the case of abutting abutment surfaces (14a, 14b). The invention further relates to a method for mounting such a component system (10) and a turbomachine with such a component system (10).
Description
Die Erfindung betrifft ein Bauteilsystem einer Turbomaschine, insbesondere einer Flugzeugturbine. Die Erfindung betrifft weiterhin ein Verfahren zum Montieren eines solchen Bauteilsystems sowie eine Turbomaschine mit einem derartigen Bauteilsystem.The invention relates to a component system of a turbomachine, in particular an aircraft turbine. The invention further relates to a method for mounting such a component system and a turbomachine with such a component system.
Aus der
Zur Abdichtung derartiger Segmentstöße von Leitkränzen, Turbinenringen und dergleichen ist es weiterhin bekannt, Bauteilsegmente mit einfachen Stößen bzw. Stoßflächen zu verwenden und die Stöße durch Montage eines umlaufenden Dichtbleches über diesen Bauteilsegmenten abzudichten. Alternativ werden Bauteilsegmente mit fest angebrachten Dichtblechen verwendet, wobei die Dichtbleche auf dem jeweils angrenzenden Bauteilsegment aufliegen oder in Nuten oder Klammern gefasst sind.To seal such segment joints of Leitkränzen, turbine rings and the like, it is also known to use component segments with simple joints or abutment surfaces and seal the shocks by mounting a circumferential sealing plate on these component segments. Alternatively, component segments are used with permanently attached sealing plates, wherein the sealing plates rest on the respective adjacent component segment or are taken in grooves or brackets.
Bei allen bekannten Ausführungen wird die Abdichtwirkung allerdings stark von den verschiedenen Toleranzketten beeinflusst, so dass nur eine vergleichsweise schlechte Abdichtung der Segmentstöße erzielt werden kann. Darüber hinaus führt beispielsweise die Verwendung von einzelnen Dichtblechen zu einem hohen Montage- und Demontageaufwand und damit zu entsprechend hohen Herstellungs- und Reparaturkosten.In all known embodiments, however, the sealing effect is strongly influenced by the different tolerance chains, so that only a comparatively poor sealing of the segment joints can be achieved. In addition, for example, the use of individual sealing sheets leads to a high assembly and disassembly effort and thus to correspondingly high manufacturing and repair costs.
Aufgabe der vorliegenden Erfindung ist es, ein Bauteilsystem der eingangs genannten Art zu schaffen, welches eine verbesserte Abdichtung ermöglicht und darüber hinaus einfacher und kostengünstiger montierbar ist. Eine weitere Aufgabe der Erfindung ist es, ein Verfahren zum Montieren eines solchen Bauteilsystems sowie eine Turbomaschine mit einem derartigen Bauteilsystem zu schaffen.Object of the present invention is to provide a component system of the type mentioned, which allows an improved seal and beyond is simpler and less expensive to install. Another object of the invention is to provide a method of assembling such a component system as well as a turbomachine having such a component system.
Die Aufgaben werden erfindungsgemäß durch ein Bauteilsystem mit den Merkmalen des Patentanspruchs 1, ein Verfahren gemäß Anspruch 11 sowie durch eine Turbomaschine gemäß Patentanspruch 12 gelöst. Vorteilhafte Ausgestaltungen mit zweckmäßigen Weiterbildungen der Erfindung sind in den Unteransprüchen angegeben.The objects are achieved by a component system with the features of claim 1, a method according to claim 11 and by a turbomachine according to claim 12. Advantageous embodiments with expedient developments of the invention are specified in the subclaims.
Ein erster Aspekt der Erfindung betrifft ein Bauteilsystem, welches eine verbesserte Abdichtung ermöglicht und darüber hinaus einfacher und kostengünstiger montierbar ist, indem zumindest das erste Bauteilsegment und das zweite Bauteilsegment zur Abdichtung eines Spalts zwischen den Stoßflächen zusammen mindestens drei Überlappungselemente umfassen. Dabei ist weiterhin vorgesehen, dass jedes Überlappungselement bei aufeinander stoßenden Stoßflächen mit dem jeweils anderen Bauteilsegment in radialer Richtung überlappt, dass wenigstens zwei der Überlappungselemente am ersten Bauteilsegment ausgebildet sind, dass wenigstens eines der Überlappungselemente am zweiten Bauteilsegment ausgebildet ist und dass das Überlappungselement des zweiten Bauteilsegments bei aufeinander stoßenden Stoßflächen in axialer Richtung zwischen den Überlappungselementen des ersten Bauteilsegments angeordnet ist. Mit anderen Worten ist es im Unterschied zum Stand der Technik vorgesehen, dass Bauteilsegmente, die im montierten Zustand aneinander angrenzen, jeweils Überlappungselemente umfassen, die im montierten Zustand mit dem jeweils anderen Bauteilsegment überlappen. Diese Segmentabdichtung ist derart in die Bauteilsegmente integriert, dass je Stoß bzw. Stoßflächenpaar mindestens drei Überlappungselemente bereitgestellt werden, wobei mindestens zwei der Überlappungselemente am ersten Bauteilsegment, das heißt auf dem ersten Ufer, angebracht sind und mindestens eines der Überlappungselemente am zweiten Bauteilsegment, das heißt auf dem zweiten Ufer und zudem zwischen den zwei Überlappungselementen des ersten Bauteilsegments ausgebildet ist. Im einfachsten Fall weist das erfindungsgemäße Bauteilsystem lediglich zwei derartige Bauteilsegmente auf, die sich zu einem Ring ergänzen. Alternativ kann vorgesehen sein, dass das Bauteilsystem drei, vier, fünf, sechs, sieben, acht, neun, zehn oder mehr Bauteilsegmente aufweist, die in der vorstehend genannten Weise mit Überlappungselementen versehen sind. Grundsätzlich ergänzen sich dabei alle Bauteilsegmente des Bauteilsystems im montierten Zustand zu einem Ring, dessen Mittelachse vorzugsweise koaxial zur Achse des Rotors der Turbomaschine verläuft. Durch die wechselweise Anordnung und Abdeckung der Überlappungselemente ergibt sich der Vorteil, dass die Leckagespalte zwischen den Stoßflächen der Bauteilsegmente zumindest im Wesentlichen nur durch die Bauteilsegmente selbst, nicht aber durch weitere Bauteile bestimmt werden. Die Toleranzkette für die einzelnen Leckagespalte kann auf diese Weise stark reduziert werden. Durch die alternierende Anordnung der Überlappungselemente kann zudem erreicht werden, dass sich die Bauteilelemente zueinander fixieren und nicht durch zusätzliche Gehäuseaufnahmen oder dergleichen fixiert werden müssen. Dies erlaubt eine weitere Reduzierung der Toleranzkette und damit eine verbesserte Spaltabdichtung.A first aspect of the invention relates to a component system which allows for improved sealing and moreover is simpler and more cost-effective to assemble, in that at least the first component segment and the second component segment for sealing a gap between the abutting surfaces together comprise at least three overlapping elements. It is further provided that each overlap element overlaps in abutting abutting surfaces with the respective other component segment in the radial direction, that at least two of the overlapping elements are formed on the first component segment, that at least one of the overlapping elements is formed on the second component segment and that the overlap element of the second component segment is arranged in abutting abutting surfaces in the axial direction between the overlapping elements of the first component segment. In other words, in contrast to the prior art, it is provided that component segments, which adjoin one another in the assembled state, each comprise overlapping elements which overlap in the assembled state with the respective other component segment. This segment seal is integrated into the component segments in such a way that at least three overlapping elements are provided per joint or abutting surface pair, at least two of the overlapping elements being attached to the first component segment, ie on the first bank, and at least one of the overlapping elements on the second component segment, that is is formed on the second bank and also between the two overlapping elements of the first component segment. In the simplest case, the component system according to the invention has only two such component segments, which complement each other to form a ring. Alternatively it can be provided that the component system three, four, five, six, has seven, eight, nine, ten or more component segments, which are provided in the above manner with overlapping elements. In principle, all the component segments of the component system complement each other in the mounted state to form a ring whose center axis preferably runs coaxially to the axis of the rotor of the turbomachine. The alternate arrangement and coverage of the overlap elements has the advantage that the leakage gaps between the abutment surfaces of the component segments are determined at least substantially only by the component segments themselves, but not by other components. The tolerance chain for the individual leakage gaps can be greatly reduced in this way. Due to the alternating arrangement of the overlapping elements can also be achieved that the component elements fix each other and not need to be fixed by additional housing receptacles or the like. This allows a further reduction of the tolerance chain and thus an improved gap seal.
In einer vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass wenigstens eines der Überlappungselemente integral am betreffenden Bauteilsegment ausgebildet und/oder stoffschlüssig mit dem betreffenden Bauteilsegment verbunden ist. Auf diese Weise sind keine losen bzw. separaten Teile wie beispielsweise Dichtbleche oder dergleichen für die Abdichtung erforderlich, wodurch sowohl die Herstellung als auch die Montage bzw. die Demontage des erfindungsgemäßen Bauteilsystems erheblich vereinfacht und vergünstigt werden. Im Fall einer stoffschlüssigen Verbindung kann das betreffende Überlappungselement beispielsweise durch Schweißen, Löten und/oder Kleben am betreffenden Bauteilsegment befestigt sein.In an advantageous embodiment of the invention, it is provided that at least one of the overlap elements is integrally formed on the relevant component segment and / or is connected by a material fit to the relevant component segment. In this way, no loose or separate parts such as sealing plates or the like are required for the seal, whereby both the production and the assembly or disassembly of the component system according to the invention are considerably simplified and discounted. In the case of a cohesive connection, the overlapping element concerned may be fastened to the relevant component segment by welding, soldering and / or gluing, for example.
Weitere Vorteile ergeben sich, wenn die Überlappungselemente bei aufeinander stoßenden Stoßflächen in wenigstens zwei radial unterschiedlichen Abständen und/oder Ebenen zur Achse angeordnet sind. Hierdurch wird auf konstruktiv einfache Weise eine mechanisch besonders stabile Fügung der beiden Bauteilsegmente ermöglicht. Darüber hinaus wird auf diese Weise besonders zuverlässig verhindert, dass die Bauteilsegmente nach erfolgter Montage in radialer Richtung relativ zueinander bewegt werden können.Further advantages arise when the overlapping elements are arranged at abutting abutting surfaces in at least two radially different distances and / or planes to the axis. As a result, a mechanically particularly stable joining of the two component segments is made possible in a structurally simple manner. In addition, it is particularly reliably prevented in this way that the component segments can be moved after installation in the radial direction relative to each other.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die zwei Überlappungselemente des ersten Bauteilsegments an gegenüberliegenden Außenbereichen des ersten Bauteilsegments ausgebildet sind und/oder dass das Überlappungselement des zweiten Bauteilsegments im axial mittleren Bereich des zweiten Bauteilsegments ausgebildet ist. Neben einer selbstzentrierenden Montage kann hierdurch sichergestellt werden, dass die Bauteilsegmente weder in axialer noch in radialer Richtung, sondern nur in Umfangsrichtung relativ zueinander bewegbar sind. Weiterhin wird hierdurch eine hohe mechanische Belastbarkeit der gefügten Bauteilsegmente erzielt.In a further advantageous embodiment of the invention, it is provided that the two overlapping elements of the first component segment are formed on opposite outer regions of the first component segment and / or that the overlapping element of the second component segment is formed in the axially central region of the second component segment. In addition to a self-centering assembly can thereby be ensured that the component segments are movable relative to each other neither in the axial nor in the radial direction, but only in the circumferential direction. Furthermore, this results in a high mechanical strength of the joined component segments is achieved.
In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist vorgesehen, dass die Überlappungselemente bei aufeinander stoßenden Stoßflächen gemeinsam den Spalt zwischen den Stoßflächen zumindest im Wesentlichen abdichten. Mit anderen Worten ist es vorgesehen, dass die Überlappungselemente im montierten Zustand der Bauteilsegmente gemeinsam den Stoßspalt zumindest im Wesentlichen überdecken, wodurch eine besonders hohe Abdichtwirkung erzielt wird. Weiterhin kann vorgesehen sein, dass die Überlappungselemente, wenn sie in unterschiedlichen radialen Abständen bzw. Ebenen montiert sind, zumindest bereichsweise über- bzw. untereinander angeordnet sind. Hierdurch kann eine Art Labyrinthdichtung erzeugt werden, wodurch eine besonders hohe Dichtwirkung erzielbar ist.In a further advantageous embodiment of the invention, it is provided that the overlapping elements jointly at least abdicht the gap between the abutment surfaces in abutting abutting surfaces. In other words, it is provided that the overlapping elements in the assembled state of the component segments together at least substantially cover the impact gap, whereby a particularly high sealing effect is achieved. Furthermore, it can be provided that the overlapping elements, if they are mounted at different radial distances or planes, are arranged above or below each other at least in regions. In this way, a kind of labyrinth seal can be generated, whereby a particularly high sealing effect can be achieved.
Weitere Vorteile ergeben sich, wenn wenigstens eines der Überlappungselemente hakenförmig und/oder im Querschnitt rechtwinklig und/oder wannenförmig und/oder V-förmig und/oder U-förmig ausgebildet ist. Obwohl die Überlappungselemente grundsätzlich nicht in ihrer Formgebung beschränkt sind, kann durch eine hakenförmige Ausgestaltung wenigstens eines der Überlappungselemente auf konstruktiv einfache Art eine Art Clipsverbindung zwischen den Bauteilsegmenten erzeugt werden. Nach der Montage wird damit eine ungewollte relative Bewegung benachbarter Bauteilsegmente in Umfangsrichtung besonders zuverlässig vermieden. Alternativ oder zusätzlich kann wenigstens eines der Überlappungselemente rechtwinklig, V-förmig und/oder U-förmig ausgebildet sein, wodurch neben einer falloptimierten Segmentabdichtung zusätzlich eine erhöhte mechanische Stabilität sowie ein Schutz gegen unerwünschte relative Bewegungen der Bauteilsegmente gegeneinander sichergestellt werden kann.Further advantages arise when at least one of the overlapping elements is hook-shaped and / or rectangular in cross-section and / or trough-shaped and / or V-shaped and / or U-shaped. Although the overlapping elements are basically not limited in their shape, a hook-shaped configuration of at least one of the overlapping elements can be used to construct a kind of clip connection between the component segments in a structurally simple manner. After assembly, an undesired relative movement of adjacent component segments in the circumferential direction is thus avoided particularly reliably. Alternatively or additionally, at least one of the overlapping elements may be formed rectangular, V-shaped and / or U-shaped, which in addition to a falloptimierten segment seal additionally increased mechanical stability and protection against unwanted relative movements of the component segments against each other can be ensured.
Eine mechanisch besonders stabile Anbindung der Bauteilsegmente wird in weiterer Ausgestaltung der Erfindung dadurch ermöglicht, dass das erste Bauteilsegment und/oder das zweite Bauteilsegment wenigstens einen Überlappungsbereich umfasst, der komplementär zum zugeordneten Überlappungselement des jeweils anderen Bauteilsegments ausgebildet ist.A mechanically particularly stable connection of the component segments is made possible in a further embodiment of the invention in that the first component segment and / or the second Component segment comprises at least one overlap region which is complementary to the associated overlap element of the respective other component segment.
Indem das Überlappungselement des zweiten Bauteilsegments eine größere Oberfläche und/oder eine größere axiale Erstreckung aufweist als die Überlappungselemente des ersten Bauteilsegments, wird eine besonders gute Segmentabdichtung erzielt.By the overlapping element of the second component segment has a larger surface area and / or a greater axial extent than the overlapping elements of the first component segment, a particularly good segmental sealing is achieved.
Weitere Vorteile ergeben sich, wenn das erste Bauteilsegment und/oder das zweite Bauteilsegment als Leitkranzsegment und/oder als Turbinenringsegment ausgebildet ist. Hierdurch können die Vorteile des erfindungsgemäßen Bauteilsystems für die genannten Turbinenelemente realisiert werden, bei denen eine zuverlässige Abdichtung der Stoßflächen zwischen den einzelnen Bauteilsegmenten sowie eine einfache Montage und Demontage von besonders hoher Bedeutung ist.Further advantages result if the first component segment and / or the second component segment is designed as a guide ring segment and / or as a turbine ring segment. In this way, the advantages of the component system according to the invention for said turbine elements can be realized, in which a reliable sealing of the abutting surfaces between the individual component segments and a simple assembly and disassembly is of particularly high importance.
Eine geometrisch besonders exakte Herstellung bei gleichzeitig niedrigen Herstellungskosten wird in weiterer Ausgestaltung der Erfindung dadurch erzielt, dass wenigstens eines der Bauteilsegmente generativ hergestellt ist. Es kann weiterhin vorgesehen sein, dass zwei, mehrere oder alle Bauteilsegmente des Bauteilsystems generativ hergestellt sind bzw. werden.A geometrically particularly exact production with simultaneously low production costs is achieved in a further embodiment of the invention in that at least one of the component segments is produced generatively. It can furthermore be provided that two, several or all component segments of the component system are or are produced generatively.
Ein zweiter Aspekt der Erfindung betrifft ein Verfahren zum Montieren eines Bauteilsystems gemäß dem ersten Erfindungsaspekt in einer Turbomaschine, bei welchem zumindest das erste Bauteilsegment und das zweite Bauteilsegment des Bauteilsystems derart gefügt werden, dass die Stoßfläche des ersten Bauteilsegments und die Stoßfläche des zweiten Bauteilsegments aufeinander stoßen, dass die wenigstens zwei Überlappungselemente des ersten Bauteilsegments in radialer Richtung mit dem zweiten Bauteilsegment überlappen, dass das wenigstens eine Überlappungselement des zweiten Bauteilsegments in radialer Richtung mit dem ersten Bauteilsegment überlappt und dass das Überlappungselement des zweiten Bauteilsegments in axialer Richtung zwischen den zwei Überlappungselementen des ersten Bauteilsegments angeordnet wird. Im einfachsten Fall werden die wenigstens zwei Bauteilsegmente dazu aufeinander geschoben, so dass die Überlappungselemente in der vorstehend genannten Weise wechselseitig auf dem jeweils anderen Bauteilsegment zu liegen kommen. Das Bauteilsystem kann grundsätzlich innerhalb eines Gehäuses der Turbomaschine montiert oder außerhalb des Gehäuses montiert und anschließend im Verbund in das Gehäuse eingehängt bzw. eingebaut werden. Neben einer verbesserten Abdichtung des Spalts zwischen den Stoßflächen der Bauteilsegmente wird hierdurch eine besonders einfache und kostengünstige Montage des Bauteilsystems ermöglicht. Eine Demontage, beispielsweise zu Wartungs-, Reparatur- oder Überholungszwecken kann dementsprechend in umgekehrter Reihenfolge bzw. durch Auseinanderziehen der Bauteilsegmente in Umfangsrichtung vorgenommen werden. Weitere sich ergebende Merkmale und deren Vorteile sind den Beschreibungen des ersten Erfindungsaspekts zu entnehmen, wobei vorteilhafte Ausgestaltungen des ersten Erfindungsaspekts als vorteilhafte Ausgestaltungen des zweiten Erfindungsaspekts und umgekehrt anzusehen sind.A second aspect of the invention relates to a method for mounting a component system according to the first aspect of the invention in a turbomachine, in which at least the first component segment and the second component segment of the component system are joined such that the abutment surface of the first component segment and the abutment surface of the second component segment abut each other in that the at least two overlapping elements of the first component segment overlap in the radial direction with the second component segment, that the at least one overlapping element of the second component segment overlaps in the radial direction with the first component segment, and in that the overlapping element of the second component segment extends axially between the two overlap elements of the first component segment Component segment is arranged. In the simplest case, the at least two component segments are pushed toward one another, so that the overlapping elements come to lie alternately on the respective other component segment in the aforementioned manner. The component system can basically be mounted inside a housing of the turbomachinery or outside be mounted and then mounted in the composite in the housing or installed. In addition to an improved sealing of the gap between the abutting surfaces of the component segments thereby a particularly simple and cost-effective installation of the component system is made possible. A disassembly, for example for maintenance, repair or overhaul purposes can accordingly be made in the reverse order or by pulling the component segments in the circumferential direction. Further resulting features and their advantages can be found in the descriptions of the first aspect of the invention, wherein advantageous embodiments of the first aspect of the invention are to be regarded as advantageous embodiments of the second aspect of the invention and vice versa.
Ein dritter Aspekt der Erfindung betrifft eine Turbomaschine, insbesondere ein Flugzeug-triebwerk, welches ein Bauteilsystem umfasst, das gemäß dem ersten Erfindungsaspekt ausgebildet und/oder mittels eines Verfahrens gemäß dem zweiten Erfindungsaspekt montiert ist. Die sich hieraus ergebenden Merkmale und deren Vorteile sind den Beschreibungen des ersten und des zweiten Erfindungsaspekts zu entnehmen, wobei vorteilhafte Ausgestaltungen des ersten und des zweiten Erfindungsaspekts als vorteilhafte Ausgestaltungen des dritten Erfindungsaspekts und umgekehrt anzusehen sind.A third aspect of the invention relates to a turbomachine, in particular an aircraft engine, which comprises a component system which is designed according to the first aspect of the invention and / or is mounted by means of a method according to the second aspect of the invention. The resulting features and their advantages are described in the descriptions of the first and second aspect of the invention, with advantageous embodiments of the first and second aspects of the invention are to be regarded as advantageous embodiments of the third aspect of the invention and vice versa.
Weitere Merkmale der Erfindung ergeben sich aus den Ansprüchen, den Ausführungsbeispielen sowie anhand der Zeichnungen. Die vorstehend in der Beschreibung genannten Merkmale und Merkmalskombinationen sowie die nachfolgend in den Ausführungsbeispielen genannten Merkmale und Merkmalskombinationen sind nicht nur in der jeweils angegebenen Kombination, sondern auch in anderen Kombinationen verwendbar, ohne den Rahmen der Erfindung zu verlassen. Dabei zeigt:
- Fig. 1
- eine schematische Perspektivansicht von zwei Bauteilsegmenten eines erfindungsgemäßen Bauteilsystems gemäß einer ersten Ausführungsform; und
- Fig. 2
- eine schematische Perspektivansicht von zwei Bauteilsegmenten des erfindungsgemäßen Bauteilsystems gemäß einer zweiten Ausführungsform.
- Fig. 1
- a schematic perspective view of two component segments of a component system according to the invention according to a first embodiment; and
- Fig. 2
- a schematic perspective view of two component segments of the component system according to the invention according to a second embodiment.
Zur Segmentabdichtung zwischen den Stoßflächen 14a, 14b weisen die Bauteilsegmente 12a, 12b für jede Stoßflächenpaarung insgesamt drei Überlappungselemente 16a-c auf. Man erkennt, dass die Überlappungselemente 16a-c bei aufeinander stoßenden Stoßflächen 14a, 14b mit dem jeweils anderen Bauteilsegment 12a, 12b in radialer Richtung überlappen, so dass die Bauteilsegmente 12a, 12b nur noch in Umfangsrichtung, nicht aber in axialer oder radialer Richtung relativ zueinander bewegt werden können. Dabei kommt das Überlappungselement 16a gemäß Pfeil Ia auf dem zugeordneten, komplementär ausgebildeten Überlappungsbereich 18a zu liegen, das Überlappungselement 16b kommt gemäß Pfeil Ib auf dem zugeordneten, komplementär ausgebildeten Überlappungsbereich 18b zu liegen und das Überlappungselement 16c kommt gemäß Pfeil Ic auf dem zugeordneten, komplementär ausgebildeten Überlappungsbereich 18c zu liegen. Wie man weiterhin erkennt, sind alle Überlappungselemente 16a-c integral mit dem jeweiligen Bauteilsegment 12a, 12b ausgebildet. Dies kann beispielsweise durch eine generative Fertigung der Bauteilsegmente 12a, 12b besonders einfach und kostengünstig erreicht werden. Weiterhin wird aus
Claims (12)
Applications Claiming Priority (1)
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DE102013219024.7A DE102013219024A1 (en) | 2013-09-23 | 2013-09-23 | Component system of a turbomachine |
Publications (2)
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EP2851518A1 true EP2851518A1 (en) | 2015-03-25 |
EP2851518B1 EP2851518B1 (en) | 2019-04-03 |
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EP14185872.0A Not-in-force EP2851518B1 (en) | 2013-09-23 | 2014-09-23 | Component system of a turbo engine |
Country Status (4)
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US (1) | US10047618B2 (en) |
EP (1) | EP2851518B1 (en) |
DE (1) | DE102013219024A1 (en) |
ES (1) | ES2724903T3 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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EP3363994A1 (en) * | 2017-02-17 | 2018-08-22 | MTU Aero Engines GmbH | Seal assembly for a gas turbine |
WO2019109197A1 (en) * | 2017-12-04 | 2019-06-13 | 贵州智慧能源科技有限公司 | Turbine housing |
Families Citing this family (6)
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US10202857B2 (en) | 2015-02-06 | 2019-02-12 | United Technologies Corporation | Vane stages |
EP3228826B1 (en) | 2016-04-05 | 2021-03-17 | MTU Aero Engines GmbH | Seal segment arrangement having a connector, corresponding gas turbine engine and method of manufacturing |
DE102017211316A1 (en) * | 2017-07-04 | 2019-01-10 | MTU Aero Engines AG | Turbomachinery sealing ring |
DE102018210600A1 (en) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | COAT RING ARRANGEMENT FOR A FLOWING MACHINE |
DE102021100071A1 (en) | 2021-01-05 | 2022-07-07 | Doosan Heavy Industries & Construction Co., Ltd. | Gas turbine ring assembly comprising ring segments with integral connecting seal |
DE102022205646A1 (en) | 2022-06-02 | 2023-12-07 | Siemens Energy Global GmbH & Co. KG | Sealing ring with overlapping sealing parts and rotor arrangement with such |
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2013
- 2013-09-23 DE DE102013219024.7A patent/DE102013219024A1/en not_active Withdrawn
-
2014
- 2014-09-23 US US14/494,011 patent/US10047618B2/en active Active
- 2014-09-23 EP EP14185872.0A patent/EP2851518B1/en not_active Not-in-force
- 2014-09-23 ES ES14185872T patent/ES2724903T3/en active Active
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WO2019109197A1 (en) * | 2017-12-04 | 2019-06-13 | 贵州智慧能源科技有限公司 | Turbine housing |
Also Published As
Publication number | Publication date |
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ES2724903T3 (en) | 2019-09-17 |
DE102013219024A1 (en) | 2015-04-09 |
EP2851518B1 (en) | 2019-04-03 |
US20150086331A1 (en) | 2015-03-26 |
US10047618B2 (en) | 2018-08-14 |
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