EP1714007B1 - Device for suspending guide blades - Google Patents

Device for suspending guide blades Download PDF

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Publication number
EP1714007B1
EP1714007B1 EP04802944.1A EP04802944A EP1714007B1 EP 1714007 B1 EP1714007 B1 EP 1714007B1 EP 04802944 A EP04802944 A EP 04802944A EP 1714007 B1 EP1714007 B1 EP 1714007B1
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EP
European Patent Office
Prior art keywords
plate
shaped elements
elements
gas channel
shaped
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EP04802944.1A
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German (de)
French (fr)
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EP1714007A1 (en
Inventor
Stefan Morgenstern
Rudolf Stanka
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP1714007A1 publication Critical patent/EP1714007A1/en
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Classifications

    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/70—Shape

Definitions

  • the invention relates to a device for suspending gas channel elements.
  • Gas channel elements such as vanes, vane segments, gas channel plates or gas channel plate segments, serve inter alia to form a gas turbine's gas passageway and must be suspended from a gas turbine housing.
  • the gas channel elements for example the vanes, project into the gas channel at a first end and are secured at a second end to a housing of the gas turbine.
  • the attachment of the gas channel elements to the housing is effected by a device for suspending gas channel elements, which may also be referred to as a suspension device or suspension element.
  • the gas channel elements in particular the guide blades projecting into the gas channel, are subject to a high thermal stress, in particular in the area of the high-pressure turbine of a gas turbine.
  • the gas channel elements are therefore strongly heated, in particular in the area of the high-pressure turbine.
  • the housing is relatively cold, so has a low temperature.
  • the suspension elements for suspending gas channel elements on a housing of a gas turbine are thus on the one hand in contact with the relatively hot gas channel elements and on the other hand with the relatively cold housing. Therefore, in the suspension devices or suspension elements, a strong temperature gradient forms, whereby the same high thermal stresses are exposed. This can lead to stress cracks within the suspension devices and thus to a reduced life of the same.
  • the prior art devices for suspending gas channel elements on a housing of the gas turbine can not adequately accommodate the thermal stresses described above due to the differences between the relatively cold housing of the gas turbine and the relatively hot gas channel elements.
  • the known from the prior art devices for suspending gas channel elements therefore have a limited life.
  • the document US-A-2,955,294 protects a device for suspending gas channel elements, which can be integrated in a compressor housing with a burgzinnen in longitudinal section housing wall.
  • guide vanes are provided according to the cantilever principle with a thickening at the radially outer end and radially inserted from the outside into a support ring or in the housing wall and held there in a form-fitting manner.
  • the present invention is based on the problem to provide a novel, low-voltage and durable device for suspending gas channel elements.
  • the device according to the invention for the suspension of gas channel elements has first plate-shaped elements and second plate-shaped elements, wherein the first plate-shaped elements and the second plate-shaped elements are connected by approximately perpendicular to the same, web-like elements to form a burgzinnenförmigen profile with each other.
  • the first plate-shaped elements are used only for connection to the housing, the second plate-shaped elements only for connection to at least one gas channel element.
  • the thermal expansions of the gas channel elements are not transferred to the device according to the invention in such a way that the life of the device according to the invention is reduced.
  • the shape of the device according to the invention is chosen so that different expansions are intercepted within the device according to the invention at the contact area to the relatively cold housing and the contact area to the relatively hot gas channel by avoiding a rigid ring structure such that stresses due to the different thermal expansions are low and so the life of the device according to the invention is not impaired.
  • a second plate-shaped element is positioned between each two adjacent spaced in the circumferential direction of the housing first plate-shaped elements such that the second plate-shaped element is connected at opposite ends via a web-like element with one of the two adjacent first plate-shaped elements.
  • the web-like elements extend over the entire width of the first plate-shaped elements and / or the second plate-shaped elements.
  • bores are introduced into the first plate-shaped elements, into which for connection to the housing of the gas turbine housing-side, bolt-like fasteners are inserted.
  • the second plate-shaped elements can be inserted for connection to the or each gas channel element in projections of the gas channel elements associated recesses.
  • Fig. 1 shows a device 10 according to the invention for suspending gas channel elements on a housing of a gas turbine in a perspective solo view.
  • the device 10 according to the invention Fig. 1 has a plurality of first plate-shaped members 11, 12, 13, and 14 and a plurality of second plate-shaped members 15, 16, and 17.
  • the first plate-shaped members 11, 12, 13, and 14 are approximately perpendicular to the second plate-shaped members 15, 16, and 17 to the same running, web-like elements 18 connected to form a meandering or burg interior profile with each other.
  • Fig. 1 can be removed, is between two adjacent, first plate-shaped elements 11 and 12 or 12 and 13 or 13 and 14 are each a second plate-shaped elements 15 and 16 or 17 positioned.
  • Each of these second plate-shaped elements 15 and 16 or 17 is connected at opposite ends via a respective web-like element 18 with one of the two adjacent, first plate-shaped elements 11 or 12 or 12 or 13 or 13 or 14.
  • the plate-shaped elements 18 extend approximately perpendicular to the first plate-shaped elements 11 to 14 and the second plate-shaped elements 15 to 17.
  • the web-like elements 18 extend over the entire width of the first plate-shaped elements 11, 12, 13, 14 and over the entire width of the second plate-shaped elements 15, 16 and 17 at the connection area with the same.
  • the above-described, meandering or burgh-trough-shaped profiling or contouring of the device 10 according to the invention for suspending gas channel elements on a housing of a gas turbine ensures the greatest possible reduction of stresses due to temperature gradients, resulting in the thermal differences between the relatively hot gas channel elements and the relatively cold housing arise.
  • the substantially rectangular or perpendicular to the plate-shaped elements 11 to 17 extending web-like elements 18 deform by thermal stresses only in the elastic range, so that no life shortening material stress occurs.
  • Fig. 1 illustrated device 10 for suspending gas channel elements has four first plate-shaped elements 11 to 14, three second plate-shaped elements 15 to 17 and six web-like elements 18 for connecting the second plate-shaped elements 15 to 17 with the first plate-shaped elements 11 to 14.
  • Bei Use of in Fig. 1 In a gas turbine apparatus 10, a plurality of such devices 10 are assembled into an annular suspension structure to secure all required gas channel elements to the housing along the circumference of the housing.
  • the device 10 according to Fig. 1 is therefore designed as a ring segment.
  • the device 10 according to the invention serves for the suspension of gas channel elements on a housing of a gas turbine.
  • the first plate-shaped elements 11 to 14 serve to connect the device 10 according to the invention to a housing 19 of the gas turbine.
  • To connect the device 10 according to the invention with the housing 19 of the gas turbine via the first plate-shaped elements 11 to 14 holes 20 are introduced into the first plate-shaped elements 11 to 14.
  • the holes 20 are best Fig. 1 be removed. In the holes 20 engage with the housing 19 associated with the housing 19, bolt-shaped fasteners 21 for attachment.
  • the meander-shaped or burg interior contouring of the device 10 according to the invention allows in this context a very direct force flow in the direction of the arrow 22 (see in particular FIG Fig. 3 ) starting from the fastening elements 21 into the device 10 according to the invention, since the supporting elements of the fastening are arranged in the direct flow of force between the housing 19 and the device 10 according to the invention. In this respect, bending stresses are reduced to a minimum here in the context of the invention.
  • Fig. 2 and 3 show as such a gas channel element 23 a profiled strut, wherein a plurality of such profiled struts in a turbine bearing intermediate housing, which is also referred to as turbine center frame, form a bearing star for supporting shafts or rotors of the gas turbine.
  • a turbine bearing intermediate housing which is also referred to as turbine center frame
  • the device according to the invention can of course also be used for suspending other gas channel elements, for example gas channel plate segments or vane segments or even individual guide vanes and individual gas channel plates.
  • Fig. 2 and 3 can be removed, serve the second plate-shaped elements 15 to 17 of the connection with the gas channel element 23.
  • the second plate-shaped elements 15 to 17 in the gas channel element 23 associated recesses can be inserted.
  • An outer shroud 24 of the gas channel element 23 are assigned to it in a substantially radially outwardly extending projections 25, wherein in each of the projections 25 each have a recess 26 is introduced, in which the two outer plate-shaped elements 15 and 17 are plugged.
  • the gas channel element 23 is thus hooked on the recesses 26 in the second plate-shaped elements 15 and 17.
  • the middle, second plate-shaped element 16 is associated with a radially inwardly extending guide pin 27.
  • the guide pin 27 engages in a corresponding recess 28 which is associated with the outer cover tape 24 of the gas channel element 23.
  • a peripheral fixing or circumferential centering of the gas channel element 23 is possible.
  • connection of the gas channel element 23 with the device 10 according to the invention has the advantage that fastening elements projecting into the gas channel, such as screws, in which large thermal stresses are then induced, can be avoided.
  • attachment described above allows a relative movement between the gas channel element 23 and the device 10 according to the invention. This relative movement causes an improved reduction of thermal circumferential stresses and can take over the function of a floating bearing in the flow direction.
  • the device according to the invention described above can be produced in one piece as a casting by simple means. Due to the one-piece design of the device 10 according to the invention an easy installation of the same is possible.

Description

Die Erfindung betrifft eine Vorrichtung zur Aufhängung von Gaskanalelementen.The invention relates to a device for suspending gas channel elements.

Gaskanalelemente, wie zum Beispiel Leitschaufeln, Leitschaufelsegmente, Gaskanalplatten oder Gaskanalplattensegmente, dienen unter anderem der Bildung eines Strömungskanals bzw. Gaskanals der Gasturbine und müssen an einem Gehäuse der Gasturbine aufgehängt bzw. befestigt werden. Die Gaskanalelemente, zum Beispiel die Leitschaufeln, ragen mit einem ersten Ende in den Gaskanal hinein und werden mit einem zweiten Ende an einem Gehäuse der Gasturbine befestigt. Die Befestigung der Gaskanalelemente an dem Gehäuse erfolgt durch eine Vorrichtung zur Aufhängung von Gaskanalelementen, die auch als Aufhängungsvorrichtung bzw. Aufhängungselement bezeichnet werden kann.Gas channel elements, such as vanes, vane segments, gas channel plates or gas channel plate segments, serve inter alia to form a gas turbine's gas passageway and must be suspended from a gas turbine housing. The gas channel elements, for example the vanes, project into the gas channel at a first end and are secured at a second end to a housing of the gas turbine. The attachment of the gas channel elements to the housing is effected by a device for suspending gas channel elements, which may also be referred to as a suspension device or suspension element.

Die Gaskanalelemente, insbesondere die in den Gaskanal hineinragenden Leitschaufeln, unterliegen insbesondere im Bereich der Hochdruckturbine einer Gasturbine einer starken thermischen Beanspruchung. Die Gaskanalelemente werden demnach insbesondere im Bereich der Hochdruckturbine stark erhitzt. Demgegenüber ist das Gehäuse relativ kalt, verfügt also über eine geringe Temperatur. Die Aufhängungselemente zur Aufhängung von Gaskanalelementen an einem Gehäuse einer Gasturbine stehen demnach einerseits mit den relativ heißen Gaskanalelementen und andererseits mit dem relativ kalten Gehäuse in Kontakt. Daher bildet sich in den Aufhängungsvorrichtungen bzw. Aufhängungselementen ein starker Temperaturgradient aus, wodurch dieselben hohen thermischen Spannungen ausgesetzt sind. Dies kann zu Spannungsrissen innerhalb der Aufhängungsvorrichtungen und damit zu einer reduzierten Lebensdauer derselben führen.The gas channel elements, in particular the guide blades projecting into the gas channel, are subject to a high thermal stress, in particular in the area of the high-pressure turbine of a gas turbine. The gas channel elements are therefore strongly heated, in particular in the area of the high-pressure turbine. In contrast, the housing is relatively cold, so has a low temperature. The suspension elements for suspending gas channel elements on a housing of a gas turbine are thus on the one hand in contact with the relatively hot gas channel elements and on the other hand with the relatively cold housing. Therefore, in the suspension devices or suspension elements, a strong temperature gradient forms, whereby the same high thermal stresses are exposed. This can lead to stress cracks within the suspension devices and thus to a reduced life of the same.

Die aus dem Stand der Technik bekannten Vorrichtungen zur Aufhängung von Gaskanalelementen an einem Gehäuse der Gasturbine können die oben beschriebenen, thermischen Spannungen aufgrund der Unterschiede zwischen dem relativ kalten Gehäuse der Gasturbine und den relativ heißen Gaskanalelementen nur unzureichend aufnehmen. Die aus dem Stand der Technik bekannten Vorrichtungen zur Aufhängung von Gaskanalelementen verfügen demnach über eine begrenzte Lebensdauer.The prior art devices for suspending gas channel elements on a housing of the gas turbine can not adequately accommodate the thermal stresses described above due to the differences between the relatively cold housing of the gas turbine and the relatively hot gas channel elements. The known from the prior art devices for suspending gas channel elements therefore have a limited life.

Die Dokumente US-A-4 832 568 , US-A-4 655 682 und EP-A-0 843 090 betreffen Vorrichtungen zur Aufhängung von Gaskanalelementen, wobei diese Vorrichtungen burgzinnenförmige Strukturen zur Verbindung der Gaskanalelemente miteinander bzw. mit zugehörigen Gehäusen verwenden. Dabei sind einerseits die genannten Strukturen durch ihre Wanddicke bzw. durch zusätzliche Elemente, wie Blechschalen, Rippen, Stirnwände etc. so versteift, dass eine spannungsarme, thermische Verformung nicht möglich ist. Andererseits ist die Anbindung der Gaskanalelemente an diese Strukturen spannungserhöhend.The documents U.S. Patent 4,832,568 . US-A-4,655,682 and EP-A-0 843 090 relate to devices for suspending gas channel elements, said devices use burgzinnenförmige structures for connecting the gas channel elements together or with associated housings. In this case, on the one hand, the structures mentioned by their wall thickness or by additional elements such as sheet metal shells, ribs, end walls, etc. stiffened so that a low-tension, thermal deformation is not possible. On the other hand, the connection of the gas channel elements to these structures is voltage-increasing.

Das Dokument US-A-2 955 294 schützt eine Vorrichtung zur Aufhängung von Gaskanalelementen, welche in ein Verdichtergehäuse mit einer im Längsschnitt burgzinnenförmigen Gehäusewand integriert sein kann. Dabei sind Leitschaufeln nach dem Cantilever-Prinzip mit einer Aufdickung am radial äußeren Ende versehen und radial von Außen in einen Tragring bzw. in die Gehäusewand gesteckt und dort formschlüssig gehalten.The document US-A-2,955,294 protects a device for suspending gas channel elements, which can be integrated in a compressor housing with a burgzinnen in longitudinal section housing wall. In this case, guide vanes are provided according to the cantilever principle with a thickening at the radially outer end and radially inserted from the outside into a support ring or in the housing wall and held there in a form-fitting manner.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige, spannungsarme und langlebige Vorrichtung zur Aufhängung von Gaskanalelementen zu schaffen.On this basis, the present invention is based on the problem to provide a novel, low-voltage and durable device for suspending gas channel elements.

Dieses Problem wird durch eine Vorrichtung zur Aufhängung von Gaskanalelementen gemäß Patentanspruch 1 gelöst. Die erfindungsgemäße Vorrichtung zur Aufhängung von Gaskanalelementen weist erste plattenförmige Elemente und zweite plattenförmige Elementen auf, wobei die ersten plattenförmigen Elemente und die zweiten plattenförmigen Elemente durch in etwa senkrecht zu denselben verlaufende, stegartige Elemente unter Bildung eines burgzinnenförmigen Profils miteinander verbunden sind. Dabei dienen die ersten plattenförmigen Elemente nur der Verbindung mit dem Gehäuse, die zweiten plattenförmigen Elemente nur der Verbindung mit mindestens einem Gaskanalelement.This problem is solved by a device for suspending gas channel elements according to claim 1. The device according to the invention for the suspension of gas channel elements has first plate-shaped elements and second plate-shaped elements, wherein the first plate-shaped elements and the second plate-shaped elements are connected by approximately perpendicular to the same, web-like elements to form a burgzinnenförmigen profile with each other. The first plate-shaped elements are used only for connection to the housing, the second plate-shaped elements only for connection to at least one gas channel element.

Mit der erfindungsgemäßen Vorrichtung zur Aufhängung von Gaskanalelementen wird zum einen erreicht, dass die thermischen Ausdehnungen der Gaskanalelemente sich nicht auf die erfindungsgemäße Vorrichtung in der Weise übertragen, dass die Lebensdauer der erfindungsgemäßen Vorrichtung verringert wird. Zum anderen ist die Form der erfindungsgemäßen Vorrichtung so gewählt, dass unterschiedliche Ausdehnungen innerhalb der erfindungsgemäßen Vorrichtung am Kontaktbereich zum relativ kalten Gehäuse und am Kontaktbereich zum relativ heißen Gaskanal durch die Vermeidung einer steifen Ringstruktur derart abgefangen werden, dass Spannungen infolge der unterschiedlichen thermischen Ausdehnungen gering sind und so die Lebensdauer der erfindungsgemäßen Vorrichtung nicht beeinträchtigt wird. Dabei ist zwischen jeweils zwei benachbarten, in Umfangsrichtung des Gehäuses beabstandeten ersten plattenförmigen Elementen jeweils ein zweites plattenförmiges Element derart positioniert, dass das zweite plattenförmige Element an gegenüberliegenden Enden über jeweils ein stegartiges Element mit jeweils einem der beiden benachbarten, ersten plattenförmigen Elemente verbunden ist.With the device according to the invention for suspending gas channel elements, on the one hand, the thermal expansions of the gas channel elements are not transferred to the device according to the invention in such a way that the life of the device according to the invention is reduced. On the other hand, the shape of the device according to the invention is chosen so that different expansions are intercepted within the device according to the invention at the contact area to the relatively cold housing and the contact area to the relatively hot gas channel by avoiding a rigid ring structure such that stresses due to the different thermal expansions are low and so the life of the device according to the invention is not impaired. In this case, a second plate-shaped element is positioned between each two adjacent spaced in the circumferential direction of the housing first plate-shaped elements such that the second plate-shaped element is connected at opposite ends via a web-like element with one of the two adjacent first plate-shaped elements.

Vorzugsweise erstrecken sich die stegartigen Elemente über die gesamte Breite der ersten plattenförmigen Elemente und/oder der zweiten plattenförmigen Elemente.Preferably, the web-like elements extend over the entire width of the first plate-shaped elements and / or the second plate-shaped elements.

Nach einer vorteilhaften Weiterbildung der Erfindung sind in die ersten plattenförmigen Elemente Bohrungen eingebracht, in die zur Verbindung mit dem Gehäuse der Gasturbine gehäuseseitige, bolzenartige Befestigungselemente einführbar sind. Die zweiten plattenförmigen Elemente sind zur Verbindung mit dem oder jedem Gaskanalelement in Vorsprüngen der Gaskanalelemente zugeordnete Ausnehmungen einsteckbar.According to an advantageous embodiment of the invention, bores are introduced into the first plate-shaped elements, into which for connection to the housing of the gas turbine housing-side, bolt-like fasteners are inserted. The second plate-shaped elements can be inserted for connection to the or each gas channel element in projections of the gas channel elements associated recesses.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
eine perspektivische Darstellung einer erfindungsgemäßen Vorrichtung zur Aufhängung von Gaskanalelementen;
Fig. 2
die erfindungsgemäße Vorrichtung zur Aufhängung von Gaskanalelementen zusammen mit einem Gaskanalelement und einem Gehäuse einer Gasturbine; und
Fig. 3
einen Querschnitt durch die Anordnung gemäß Fig. 2.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a perspective view of an apparatus for suspending gas channel elements according to the invention;
Fig. 2
the device according to the invention for the suspension of gas channel elements together with a gas channel element and a housing of a gas turbine; and
Fig. 3
a cross section through the arrangement according to Fig. 2 ,

Fig. 1 zeigt eine erfindungsgemäße Vorrichtung 10 zur Aufhängung von Gaskanalelementen an einem Gehäuse einer Gasturbine in einer perspektivischen Alleindarstellung. Die erfindungsgemäße Vorrichtung 10 gemäß Fig. 1 verfügt über mehrere erste plattenförmige Elemente 11, 12, 13 und 14 und mehrere zweite plattenförmige Elemente 15, 16 und 17. Die ersten plattenförmigen Elemente 11, 12, 13 und 14 sind mit den zweiten plattenförmigen Elementen 15, 16 und 17 durch in etwa senkrecht zu denselben verlaufende, stegartige Elemente 18 unter Bildung eines mäanderförmigen oder burgzinnenförmigen Profils miteinander verbunden. Fig. 1 shows a device 10 according to the invention for suspending gas channel elements on a housing of a gas turbine in a perspective solo view. The device 10 according to the invention Fig. 1 has a plurality of first plate-shaped members 11, 12, 13, and 14 and a plurality of second plate-shaped members 15, 16, and 17. The first plate-shaped members 11, 12, 13, and 14 are approximately perpendicular to the second plate-shaped members 15, 16, and 17 to the same running, web-like elements 18 connected to form a meandering or burg interior profile with each other.

Wie Fig. 1 entnommen werden kann, ist zwischen zwei benachbarten, ersten plattenförmigen Elementen 11 und 12 bzw. 12 und 13 bzw. 13 und 14 jeweils ein zweites plattenförmiges Elemente 15 bzw. 16 bzw. 17 positioniert. Jedes dieser zweiten plattenförmigen Elemente 15 bzw. 16 bzw. 17 ist an gegenüberliegenden Enden über jeweils ein stegartiges Element 18 mit einem der beiden benachbarten, ersten plattenförmigen Elemente 11 oder 12 bzw. 12 oder 13 bzw. 13 oder 14 verbunden. Wie bereits erwähnt, verlaufen die plattenförmigen Elementen 18 in etwa senkrecht zu den ersten plattenförmigen Elementen 11 bis 14 und den zweiten plattenförmigen Elementen 15 bis 17. Die stegartigen Elemente 18 erstrecken sich dabei über die gesamte Breite der ersten plattenförmigen Elemente 11, 12, 13, 14 sowie über die gesamte Breite der zweiten plattenförmigen Elemente 15, 16 bzw. 17 am Verbindungsbereich mit denselben.As Fig. 1 can be removed, is between two adjacent, first plate-shaped elements 11 and 12 or 12 and 13 or 13 and 14 are each a second plate-shaped elements 15 and 16 or 17 positioned. Each of these second plate-shaped elements 15 and 16 or 17 is connected at opposite ends via a respective web-like element 18 with one of the two adjacent, first plate-shaped elements 11 or 12 or 12 or 13 or 13 or 14. As already mentioned, the plate-shaped elements 18 extend approximately perpendicular to the first plate-shaped elements 11 to 14 and the second plate-shaped elements 15 to 17. The web-like elements 18 extend over the entire width of the first plate-shaped elements 11, 12, 13, 14 and over the entire width of the second plate-shaped elements 15, 16 and 17 at the connection area with the same.

Die oben beschriebene, mäanderförmige bzw. burgzinnenförmige Profilierung bzw. Konturierung der erfindungsgemäßen Vorrichtung 10 zur Aufhängung von Gaskanalelementen an einem Gehäuse einer Gasturbine gewährleistet einen größtmöglichen Abbau von Spannungen infolge von Temperaturgradienten, welche bei den thermischen Unterschieden zwischen den relativ heißen Gaskanalelementen und dem relativ kalten Gehäuse entstehen. Die im Wesentlichen rechtwinklig bzw. senkrecht zu den plattenförmigen Elementen 11 bis 17 verlaufenden, stegartigen Elemente 18 verformen sich durch thermische Belastungen nur im elastischen Bereich, sodass keine Lebensdauer verkürzende Materialbeanspruchung auftritt.The above-described, meandering or burgh-trough-shaped profiling or contouring of the device 10 according to the invention for suspending gas channel elements on a housing of a gas turbine ensures the greatest possible reduction of stresses due to temperature gradients, resulting in the thermal differences between the relatively hot gas channel elements and the relatively cold housing arise. The substantially rectangular or perpendicular to the plate-shaped elements 11 to 17 extending web-like elements 18 deform by thermal stresses only in the elastic range, so that no life shortening material stress occurs.

In diesem Zusammenhang sei angemerkt, dass es vorteilhaft ist, die stegartigen Elemente, die der Verbindung der ersten plattenförmigen Elemente 11 bis 14 mit den zweiten plattenförmigen Elementen 15 bis 17 dienen, so lang wie möglich auszugestalten. Dadurch können die thermischen Spannungen in der erfindungsgemäßen Vorrichtung 10 besonders gut abgebaut werden.In this connection, it should be noted that it is preferable to make the web-like members serving as the connection of the first plate-shaped members 11 to 14 with the second plate-shaped members 15 to 17 as long as possible. As a result, the thermal stresses in the device 10 according to the invention can be broken down particularly well.

Die in Fig. 1 dargestellte, erfindungsgemäße Vorrichtung 10 zur Aufhängung von Gaskanalelementen verfügt über vier erste plattenförmige Elemente 11 bis 14, drei zweite plattenförmige Elemente 15 bis 17 und sechs stegartige Elemente 18 zur Verbindung der zweiten plattenförmigen Elemente 15 bis 17 mit den ersten plattenförmigen Elementen 11 bis 14. Bei Verwendung der in Fig. 1 dargestellten Vorrichtung 10 in einer Gasturbine werden mehrere derartige Vorrichtungen 10 zu einer ringförmigen Aufhängungsstruktur zusammengefügt, um entlang des Umfangs des Gehäuses alle erforderlichen Gaskanalelemente am Gehäuse zu befestigen. Die Vorrichtung 10 gemäß Fig. 1 ist demzufolge als Ringsegment ausgeführt. Im Unterschied zum gezeigten Ausführungsbeispiel ist es auch möglich, die erfindungsgemäße Vorrichtung 10 unmittelbar in Form eines Ringes auszubilden.In the Fig. 1 illustrated device 10 for suspending gas channel elements has four first plate-shaped elements 11 to 14, three second plate-shaped elements 15 to 17 and six web-like elements 18 for connecting the second plate-shaped elements 15 to 17 with the first plate-shaped elements 11 to 14. Bei Use of in Fig. 1 In a gas turbine apparatus 10, a plurality of such devices 10 are assembled into an annular suspension structure to secure all required gas channel elements to the housing along the circumference of the housing. The device 10 according to Fig. 1 is therefore designed as a ring segment. In contrast to the embodiment shown, it is also possible to form the device 10 according to the invention directly in the form of a ring.

Wie bereits mehrfach erwähnt, dient die erfindungsgemäße Vorrichtung 10 der Aufhängung von Gaskanalelementen an einem Gehäuse einer Gasturbine. Die ersten plattenförmigen Elemente 11 bis 14 dienen dabei der Verbindung der erfindungsgemäßen Vorrichtung 10 mit einem Gehäuse 19 der Gasturbine. Dies kann insbesondere Fig. 2 entnommen werden. Zur Verbindung der erfindungsgemäßen Vorrichtung 10 mit dem Gehäuse 19 der Gasturbine über die ersten plattenförmigen Elemente 11 bis 14 sind in die ersten plattenförmigen Elemente 11 bis 14 Bohrungen 20 eingebracht. Die Bohrungen 20 können am besten Fig. 1 entnommen werden. In die Bohrungen 20 greifen zur Befestigung mit dem Gehäuse 19 dem Gehäuse 19 zugeordnete, bolzenförmige Befestigungselemente 21 ein. Die mäanderförmige bzw. burgzinnenförmige Konturierung der erfindungsgemäßen Vorrichtung 10 ermöglicht in diesem Zusammenhang einen sehr direkten Kraftfluss im Sinne des Pfeils 22 (siehe insbesondere Fig. 3) ausgehend von den Befestigungselementen 21 in die erfindungsgemäße Vorrichtung 10 hinein, da die tragenden Elemente der Befestigung im direkten Kraftfluss zwischen dem Gehäuse 19 und der erfindungsgemäßen Vorrichtung 10 angeordnet sind. Insofern werden hier im Sinne der Erfindung Biegespannungen auf ein Minimum reduziert.As already mentioned several times, the device 10 according to the invention serves for the suspension of gas channel elements on a housing of a gas turbine. The first plate-shaped elements 11 to 14 serve to connect the device 10 according to the invention to a housing 19 of the gas turbine. This can be special Fig. 2 be removed. To connect the device 10 according to the invention with the housing 19 of the gas turbine via the first plate-shaped elements 11 to 14 holes 20 are introduced into the first plate-shaped elements 11 to 14. The holes 20 are best Fig. 1 be removed. In the holes 20 engage with the housing 19 associated with the housing 19, bolt-shaped fasteners 21 for attachment. The meander-shaped or burg interior contouring of the device 10 according to the invention allows in this context a very direct force flow in the direction of the arrow 22 (see in particular FIG Fig. 3 ) starting from the fastening elements 21 into the device 10 according to the invention, since the supporting elements of the fastening are arranged in the direct flow of force between the housing 19 and the device 10 according to the invention. In this respect, bending stresses are reduced to a minimum here in the context of the invention.

Die gegenüber den ersten plattenförmigen Elementen 11 bis 14 versetzt angeordneten, zweiten plattenförmigen Elemente 15 bis 17 dienen der Verbindung der erfindungsgemäßen Vorrichtung mit mindestens einem Gaskanalelement. Fig. 2 und 3 zeigen als ein derartiges Gaskanalelement 23 eine profilierte Strebe, wobei mehrere derartige, profilierte Streben in einem Turbinenlager-Zwischengehäuse, welches auch als Turbine Center Frame bezeichnet wird, einen Lagerstern zur Lagerung von Wellen bzw. Rotoren der Gasturbine bilden. An dieser Stelle sei darauf hingewiesen, dass die erfindungsgemäße Vorrichtung selbstverständlich auch zur Aufhängung anderer Gaskanalelemente, zum Beispiel von Gaskanalplattensegmenten oder Leitschaufelsegmenten oder auch einzelnen Leitschaufeln und einzelnen Gaskanalplatten, verwendet werden kann.The offset relative to the first plate-shaped elements 11 to 14, second plate-shaped elements 15 to 17 serve to connect the device according to the invention with at least one gas channel element. Fig. 2 and 3 show as such a gas channel element 23 a profiled strut, wherein a plurality of such profiled struts in a turbine bearing intermediate housing, which is also referred to as turbine center frame, form a bearing star for supporting shafts or rotors of the gas turbine. It should be noted at this point that the device according to the invention can of course also be used for suspending other gas channel elements, for example gas channel plate segments or vane segments or even individual guide vanes and individual gas channel plates.

Wie insbesondere Fig. 2 und 3 entnommen werden kann, dienen die zweiten plattenförmigen Elemente 15 bis 17 der Verbindung mit dem Gaskanalelement 23. Hierzu sind die zweiten plattenförmigen Elemente 15 bis 17 in dem Gaskanalelement 23 zugeordnete Ausnehmungen einsteckbar. Im gezeigten Ausführungsbeispiel dienen die beiden äußeren, zweiten plattenförmigen Elemente 15 und 17 der. Verbindung mit dem Gaskanalelement 23. Einem Außendeckband 24 des Gaskanalelements 23 sind hierzu sich im Wesentlichen in radialer Richtung nach außen erstreckende Vorsprünge 25 zugeordnet, wobei in jeden der Vorsprünge 25 jeweils eine Ausnehmung 26 eingebracht ist, in welche die beiden äußeren, plattenförmigen Elemente 15 und 17 einsteckbar sind. Das Gaskanalelement 23 wird demnach über die Ausnehmungen 26 in die zweiten plattenförmigen Elemente 15 und 17 eingehakt.In particular Fig. 2 and 3 can be removed, serve the second plate-shaped elements 15 to 17 of the connection with the gas channel element 23. For this purpose, the second plate-shaped elements 15 to 17 in the gas channel element 23 associated recesses can be inserted. In the embodiment shown, the two outer, second plate-shaped elements 15 and 17 of the. Connection to the gas channel element 23. An outer shroud 24 of the gas channel element 23 are assigned to it in a substantially radially outwardly extending projections 25, wherein in each of the projections 25 each have a recess 26 is introduced, in which the two outer plate-shaped elements 15 and 17 are plugged. The gas channel element 23 is thus hooked on the recesses 26 in the second plate-shaped elements 15 and 17.

Im gezeigten Ausführungsbeispiel ist dem mittleren, zweiten plattenförmigen Element 16 ein sich in radialer Richtung nach innen erstreckender Führungsstift 27 zugeordnet. Der Führungsstift 27 greift in eine entsprechende Ausnehmung 28 ein, die dem Außendeckband 24 des Gaskanalelement 23 zugeordnet ist. Über den in die Ausnehmung 28 eingreifenden Führungsstift 27 ist eine Umfangsfixierung bzw. Umfangszentrierung des Gaskanalelements 23 möglich. Wie Fig. 2 entnommen werden kann, ist in diesem Zusammenhang das mittlere, zweite plattenförmige Element 16 gegenüber den äußeren, zweiten plattenförmigen Elementen 15 bis 17 nach radial innen versetzt.In the embodiment shown, the middle, second plate-shaped element 16 is associated with a radially inwardly extending guide pin 27. The guide pin 27 engages in a corresponding recess 28 which is associated with the outer cover tape 24 of the gas channel element 23. About the engaging in the recess 28 guide pin 27 is a peripheral fixing or circumferential centering of the gas channel element 23 is possible. As Fig. 2 can be removed, in this context, the middle, second plate-shaped element 16 relative to the outer, second plate-shaped elements 15 to 17 offset radially inward.

Die obige Verbindung des Gaskanalelements 23 mit der erfindungsgemäßen Vorrichtung 10 verfügt über den Vorteil, dass in den Gaskanal hineinragende Befestigungselemente, wie zum Beispiel Schrauben, in denen dann große thermische Spannungen induziert werden, vermieden werden können. Außerdem ermöglicht die oben beschriebene Befestigung eine Relativbewegung zwischen dem Gaskanalelement 23 und der erfindungsgemäßen Vorrichtung 10. Diese Relativbewegung bewirkt einen verbesserten Abbau von thermischen Umfangsspannungen und kann die Funktion eines Loslagers in Strömungsrichtung übernehmen.The above connection of the gas channel element 23 with the device 10 according to the invention has the advantage that fastening elements projecting into the gas channel, such as screws, in which large thermal stresses are then induced, can be avoided. In addition, the attachment described above allows a relative movement between the gas channel element 23 and the device 10 according to the invention. This relative movement causes an improved reduction of thermal circumferential stresses and can take over the function of a floating bearing in the flow direction.

Die oben beschriebene, erfindungsgemäße Vorrichtung kann als Gussteil mit einfachen Mitteln einstückig hergestellt werden. Durch die einstückige Ausführung der erfindungsgemäßen Vorrichtung 10 ist eine leichte Montage derselben möglich.The device according to the invention described above can be produced in one piece as a casting by simple means. Due to the one-piece design of the device 10 according to the invention an easy installation of the same is possible.

Claims (8)

  1. A device for suspending gas channel elements (23) on a housing (19) of a gas turbine, in particular for suspending guide vanes or guide vane segments or gas channel plates or gas channel plate segments, comprising a plurality of first plate-shaped elements (11, 12, 13, 14) and a plurality of second plate-shaped elements (15, 16, 17), wherein the first plate-shaped elements (11, 12, 13, 14) and the second plate-shaped elements (15, 16, 17) are connected to one another by web-like elements (18) which extend approximately perpendicular to said plate-shaped elements, forming a crenelated profile, and wherein in each case a second plate-like element (15; 16; 17) is positioned between two adjacent first plate-shaped elements (11, 12; 12, 13; 13, 14), which are spaced apart from one another, in such a way that the second plate-like element (15; 16; 17) is connected at each of its opposing ends by means of a respective web-like element (18) to a respective one of the two adjacent first plate-shaped elements (11, 12; 12, 13; 13, 14), characterized in that in the installed state the first plate-shaped elements (11, 12, 13, 14) serve only for connection to the housing (19) of the gas turbine and the second plate-shaped elements (15, 16, 17) serve only for connection to at least one gas channel element (23), wherein the web-like elements (18) serve only for connection of the first and second plate-shaped elements.
  2. The device according to claim 1, characterized in that the web-like elements (18) extend axially over the entire width of the first plate-shaped elements (11, 12, 13, 14) and/or the second plate-shaped elements (15, 16, 17),
  3. The device according to claim 1 or 2, characterized in that it is designed as a closed ring having a crenelated profile.
  4. The device according to claim 1 or 2, characterized in that it is designed as a ring segment having a crenelated profile, wherein a plurality of such ring segments can be joined together to form a ring.
  5. The device according to claim 4, characterized in that such a ring segment has four first plate-shaped elements (11, 12, 13, 14) and three second plate-shaped elements (15, 16, 17), wherein the three second plate-shaped elements (15, 16, 17) are connected to the four first plate-shaped elements (11, 12, 13, 14) by means of a total of six web-like elements (18) extending approximately perpendicular to said second plate-shaped elements.
  6. The device according to one of claims 1 to 5, characterized in that the first plate-shaped elements (11, 12, 13, 14) have holes (20) into which bolt-like fastening elements (21) on the housing side can be inserted for connection to the housing (19) of the gas turbine.
  7. The device according to one of claims 1 to 6, characterized in that, for connection to the or each gas channel element, the second plate-shaped elements (15, 17) can be inserted into recesses (26) associated with projections (25) of the gas channel elements (23).
  8. The device according to one of claims 1 to 7, characterized in that at least one of the second plate-shaped elements (16) has a guide pin (27) for circumferential centering or circumferential fixing of a gas channel element (23).
EP04802944.1A 2004-01-09 2004-12-15 Device for suspending guide blades Active EP1714007B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004001393A DE102004001393A1 (en) 2004-01-09 2004-01-09 Device for suspending gas channel elements
PCT/DE2004/002745 WO2005066462A1 (en) 2004-01-09 2004-12-15 Device for suspending guide blades

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EP1714007A1 EP1714007A1 (en) 2006-10-25
EP1714007B1 true EP1714007B1 (en) 2016-11-09

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US9206700B2 (en) * 2013-10-25 2015-12-08 Siemens Aktiengesellschaft Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine
US10094244B2 (en) * 2015-09-18 2018-10-09 General Electric Company Ceramic matrix composite ring shroud retention methods-wiggle strip spring seal
EP3228837B1 (en) * 2016-04-08 2019-08-28 Ansaldo Energia Switzerland AG Assembly of turboengine components
ES2769074T3 (en) * 2017-06-01 2020-06-24 MTU Aero Engines AG Intermediate housing for turbine with centering element

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US3043103A (en) 1958-10-10 1962-07-10 Gen Motors Corp Liquid cooled wall
GB904138A (en) * 1959-01-23 1962-08-22 Bristol Siddeley Engines Ltd Improvements in or relating to stator structures, for example for axial flow gas turbine engines
US4361010A (en) * 1980-04-02 1982-11-30 United Technologies Corporation Combustor liner construction
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FR2646880A1 (en) * 1989-05-11 1990-11-16 Snecma THERMAL PROTECTION SHIRT FOR POST-COMBUSTION CHANNEL OR TRANSITION OF TURBOREACTOR
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WO2005066462A1 (en) 2005-07-21
US8591182B2 (en) 2013-11-26
DE102004001393A1 (en) 2005-08-04
US20080292457A1 (en) 2008-11-27
EP1714007A1 (en) 2006-10-25

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