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EP1389265B1 - Gas Turbine - Google Patents

Gas Turbine Download PDF

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Publication number
EP1389265B1
EP1389265B1 EP02729832A EP02729832A EP1389265B1 EP 1389265 B1 EP1389265 B1 EP 1389265B1 EP 02729832 A EP02729832 A EP 02729832A EP 02729832 A EP02729832 A EP 02729832A EP 1389265 B1 EP1389265 B1 EP 1389265B1
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EP
European Patent Office
Prior art keywords
gas turbine
seal support
securing element
turbine according
lining
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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EP02729832A
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German (de)
French (fr)
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EP1389265A1 (en
Inventor
Walter Gieg
Helmut Gröss
Klemens Hain
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb

Definitions

  • the invention relates to a gas turbine with a housing, with an axially flowed through low-pressure turbine and / or turbine area, with at least one blade ring with shroud and vanes in the low pressure and / or turbine area and with at least one shroud, consisting of several, in the circumferential direction lined up Segments, according to the preamble of claim 1.
  • Such a conventional embodiment of the shrouds is known for example from DE-C-27 45 130.
  • the shrouds are here with “covers (10)” or with “shroud covers (1o)” referred to, the inlet linings with “sealing surfaces (11)".
  • the housing (13) of the gas turbine has fastening elements (cylinders 14) which carry both the guide vanes (1) and the shrouds (covers 10).
  • the radially outer, upstream ends of the vanes (1) surround claws (bulges 22) of the fasteners claw-like, in the same way do the downstream ends of the shrouds.
  • US-A-4,242,042 protects a gap maintaining system for gas turbines in which cooling air is guided longitudinally on the inside of a turbine housing (10), in particular a low-pressure turbine.
  • the cooling air flow moves radially outward of the vanes and outside of the shrouds (14) surrounding shrouds.
  • the segments of the shroud rings each comprise two functional elements, namely a seal carrier (20) provided with an inlet lining and a further bowl-like element (26, 28), which only in the region of its axially front and rear end and optionally in the middle region on the seal carrier (20) is present.
  • the elements (26, 28) act as a thermally insulating shield between the hot seal carrier (20) and the air-cooled housing (10).
  • the seal carrier has at its upstream end a hook-like extension, with which it holds the radially outer end of at least one guide vane (12) in a form-fitting manner.
  • the disadvantage here is that the hook-like extension is exposed to the hot gases, so that with wear,
  • the object of the invention is to make in a gas turbine with the features of the preamble of claim 1 a segmented shroud with seal carrier function and Leitschaufelommesfunktion so that increases thermal stress relief of the Leitschaufelbefest Trentsstellen and the turbine housing mechanical strength and thus wear and plastic deformation strong be reduced or avoided.
  • the vane securing function should be met with the highest reliability.
  • each segment of the jacket ring comprises a seal carrier and a securing element.
  • the components "seal carrier” and “fuse element” touch, but they are not firmly connected.
  • the seal carrier and the securing element are designed in relation to each other so that they as possible large areas of their surfaces are spaced apart, and have only the smallest possible common, heat-conducting contact points.
  • the seal carrier approximately assumes the local hot gas temperature, whereas the securing element remains at a significantly lower temperature due to the shielding effect of the seal carrier with minimized heat conduction.
  • the housing-side guide vane fastening elements thereby remain significantly cooler during operation and are mechanically considerably higher load capacity.
  • the temperature reduction continues into the turbine housing, whereby the shielding effect of the shell-like securing element also comes into play. Additional heat insulation measures or materials are therefore generally no longer required. Due to the fact that the securing element is supported axially directly on the housing, the guide blade safety function reliably remains independent of thermal expansions of the subsequent guide blade over the entire operating range.
  • the invention will be explained in more detail with reference to the drawing.
  • the figure shows a partial longitudinal section through the outer Schaufelabdichtungs- and housing portion of a low-pressure turbine of a turbojet engine in a simplified representation.
  • the turbine region shown in the figure is the low-pressure turbine or useful turbine region, the latter in the case of a shaft power gas turbine.
  • Three-shaft engines could also be the mid-pressure turbine area.
  • the flow direction should run from left to right here, with the housing-side channel boundary rising divergently from bottom left to top right.
  • the longitudinal center axis / rotation axis of the gas turbine would run horizontally and below the image area, the hub area is also too deep to be detected by the representation.
  • the invention specifically relates to the structural design of the rotor blade tip seal, ie, the so-called O uter A ir S EFSA (OAS).
  • the sealed blade ring 11 has a shroud 12 with two sealing tips 13,14, which cooperate with a here in the diameter stepped inlet lining 6 in honeycomb structure.
  • Upstream and downstream of the blade ring 11 guide vanes 15,16 can be seen, which are statically arranged in the housing 17 of the turbine as individual parts or as combined from several blades segments.
  • the radially outer, downstream end of the vane 15 - or the vane segment - lies in a radially inwardly open, around the housing 17 extending groove 18.
  • a similar, upstream suspension also has the vane 15 (left outside of the illustration). It can be envisaged that the vane 15, without further securing measures in the housing and hub region, could release its upstream suspension (see area at pos. 19) as a "hinge” pivoting out of the groove 18 by radial movement inwards.
  • the holding and securing function of the shroud 1 which extends axially from the vane 15 to the vane 16 and in the circumferential direction around the housing 17.
  • a seal carrier 3 On the hot gas side, a seal carrier 3 is arranged here, which holds the inlet lining 6 as part of the outer air seal (OAS).
  • a securing element 7 On the housing side, a securing element 7 is present here, which secures the guide blade 15 against coming out of the groove 18 in its primary function.
  • the seal carrier 3 comprises here, in addition to the inlet lining 6, a shell-like support member 4 and a - in the axial section hook-like stop member 5. Since several such seal carrier 3 are positioned adjacent to each other over the turbine circumference, on this additional sealing elements, such as tongues, tabs etc. available be.
  • the seal carrier 3 is axially movable within certain limits, in which case the foremost position is shown with effective stop member 5. Since the sealing technically effective inner contours of the inlet lining 6 are each cylindrical and axially long enough, the axial position not critical.
  • the securing element 7 comprises an axial section C-shaped securing part 8, which engages under the groove 18 with the guide blade end, a shell-like shielding part 9 and a hook-like in axial section stop member 10.
  • the largely spaced elements 3 and 7 have defined contact points C1, C2, their extent is minimized in terms of low heat conduction, for example by periodic interruptions in the circumferential direction, which are required for mutual support.
  • the fuse element 7 acts thermally as an additional radiation shield between the hot seal carrier 3 and the housing 17. This can be dispensed with additional heat insulation in this area. It can also be seen that the hot carrier part 4 according to the invention does not bear directly on the fastening elements of the housing 17 in the region of the grooves 18 and 19. Thus, these mechanically critical areas are also thermally relieved. In this connection, it is possible to produce only the part 4 for thermal reasons from a cobalt alloy, the parts 5,6,8,9 and 10 may consist of manufacturing and wear technically good-natured nickel alloys or even steels. For fixed connections within parts 3 and 7, brazing is provided exclusively using suitable high-temperature solders.
  • the seal carrier 3 and / or the securing element 7 can also each be produced integrally as a turned part from a forged ring or as a cast part. Due to the segmented design of the shroud 1, the parts 3 and 7 themselves represent segments, which are juxtaposed in larger numbers over the housing circumference. It may be useful to move the butt joints of the parts 7 relative to those of the parts 3 in the circumferential direction.
  • the invention does not assume that a vane ring follows downstream of the shell ring, as shown in the figure. It can e.g. also a Gesimouseliner the constructive and fluidic continuation of the shroud with support and stop function for the latter form.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft eine Gasturbine mit einem Gehäuse, mit einem axial durchströmten Niederdruckturbinenbereich und/oder Nutzturbinenbereich, mit wenigstens einem Laufschaufelkranz mit Deckband sowie mit Leitschaufeln in dem Niederdruck- und/oder Nutzturbinenbereich und mit wenigstens einem Mantelring, bestehend aus mehreren, in Umfangsrichtung aneinander gereihten Segmenten, gemäß dem Oberbegriff des Patentanspruches 1.The invention relates to a gas turbine with a housing, with an axially flowed through low-pressure turbine and / or turbine area, with at least one blade ring with shroud and vanes in the low pressure and / or turbine area and with at least one shroud, consisting of several, in the circumferential direction lined up Segments, according to the preamble of claim 1.

Bei Niederdruck- und Nutzturbinen von Gasturbinen für Luft-, Land- und Wasserfahrzeuge sowie für stationären Einsatz sind über den Laufschaufeln segmentierte Mantelringe (Outer Air Seals, OAS) angeordnet, die folgende Aufgaben haben:

  • Abschirmung des Gehäuses der Gasturbine von den hohen Gastemperaturen,
  • Bereitstellung eines Einlaufbelages für die Dichtspitzen am Laufschaufeldeckband, und
  • oft auch Sicherung der stromauf angeordneten Leitschaufel-Stufe im Gehäuse durch Formschluss.
For low-pressure and utility turbines of gas turbines for air, land and water vehicles as well as for stationary use segmented Outer Air Seals (OAS) are arranged above the blades, which have the following tasks:
  • Shielding the housing of the gas turbine from the high gas temperatures,
  • Providing an inlet covering for the sealing tips on the blade cover, and
  • often also securing the upstream vane stage in the housing by positive locking.

Gemäß dem Stand der Technik werden zumindest die beiden letzteren Aufgaben von einem Bauteil übernommen, d.h. vom jeweiligen Mantelring-Segment. Zur Erfüllung der ersten Aufgabe ist es oft erforderlich, zusätzliches Wärmeisolationsmaterial zwischen dem Mantelring und dem diesen von außen umschließenden Gasturbinengehäuse anzuordnen, was die Kosten, das Gewicht und den Montageaufwand erhöht.According to the prior art, at least the latter two objects are taken over by a component, i. from the respective shroud segment. In order to accomplish the first object, it is often necessary to arrange additional heat insulation material between the shroud and the gas turbine housing surrounding the same from the outside, which increases the cost, the weight and the assembly effort.

Durch den hohen Wärmeübergang vom Einlaufbelag, meist einer Honigwabenstruktur, in die Mantelring-Segmente, die ja auch die Leitschaufel-Sicherungsfunktion erfüllen, werden die Segmente sehr heiß mit folgenden negativen Auswirkungen:

  • Aufheizung der Leitschaufel-Befestigungselemente am Gehäuse sowie des Gehäuses selbst durch direkten, wärmeleitenden Kontakt,
  • Abfall der Festigkeit und des Verschleißwiderstandes der aufgeheizten Teile,
  • Maßänderungen und Relativbewegungen im Bereich der Leitschaufelsicherung, somit Verschleiß und die Erfordernis großer Spiele insbesondere in Axialrichtung.
Due to the high heat transfer from the inlet lining, usually a honeycomb structure, into the shroud segments, which also fulfill the guide blade safety function, the segments become very hot with the following negative effects:
  • Heating the guide vane fastening elements on the housing and of the housing itself by direct, heat-conducting contact,
  • Decrease in the strength and wear resistance of the heated parts,
  • Dimensional changes and relative movements in the area of the vane securing, thus wear and the requirement of large games, especially in the axial direction.

Die Kombination der beiden letztgenannten Effekte hat in einigen Fällen dazu geführt, dass infolge von plastischen Verformungen die Leitschaufel- Sicherungsfunktion versagte und somit eine oder mehrere Leitschaufeln im Betrieb frei wurden mit der Folge starker Beschädigung bzw. der Zerstörung des betroffenen Turbinenbereichs.The combination of the two last-mentioned effects has in some cases led to the failure of the vane securing function as a result of plastic deformations and thus of one or more vanes being released during operation, resulting in severe damage or destruction of the affected turbine region.

Eine solche, konventionelle Ausführung der Mantelringe ist beispielsweise aus der DE-C-27 45 130 bekannt. Die Mantelringe sind hier mit "Abdeckungen (10)" oder mit "Mantelringabdeckungen (1o)" bezeichnet, die Einlaufbeläge mit "Dichtflächen (11)". Das Gehäuse (13) der Gasturbine weist Befestigungselemente (Zylinder 14) auf, welche sowohl die Leitschaufeln (1) als auch die Mantelringe (Abdeckungen 10) tragen. Die radial äußeren, stromaufwärtigen Enden der Leitschaufeln (1) umgreifen Verdickungen (Wulste 22) der Befestigungselemente klauenartig, in gleicher Weise tun dies die stromabwärtigen Enden der Mantelringe. Die radial äußeren, stromabwärtigen Enden der Leitschaufeln (1) liegen radial von innen an den Befestigungselementen (Zylindern 14) an und werden von den klauenartigen, stromaufwärtigen Enden der Mantelringe formschlüssig gesichert. Somit liegen konstruktionsbedingt auch hier die bereits geschilderten, thermischen und mechanischen Probleme vor.Such a conventional embodiment of the shrouds is known for example from DE-C-27 45 130. The shrouds are here with "covers (10)" or with "shroud covers (1o)" referred to, the inlet linings with "sealing surfaces (11)". The housing (13) of the gas turbine has fastening elements (cylinders 14) which carry both the guide vanes (1) and the shrouds (covers 10). The radially outer, upstream ends of the vanes (1) surround claws (bulges 22) of the fasteners claw-like, in the same way do the downstream ends of the shrouds. The radially outer, downstream ends of the vanes (1) abut radially from the inside to the fastening elements (cylinders 14) and are positively secured by the claw-like, upstream ends of the shrouds. Thus, due to the design, the already described thermal and mechanical problems also exist here.

Die US-A-4 242 042 schützt ein Spalthaltungssystem für Gasturbinen, bei dem Kühlluft an der Innenseite eines Turbinengehäuses (10), insbesondere einer Niederdruckturbine, in Längsrichtung geführt wird. Der Kühlluftstrom bewegt sich radial außerhalb der Leitschaufelenden und außerhalb der die Laufschaufeln (14) umgebenden Mantelringe. Die Segmente der Mantelringe umfassen jeweils zwei Funktionselemente, nämlich einen mit einem Einlaufbelag versehenen Dichtungsträger (20) und ein weiteres, schalenartiges Element (26, 28), welches nur im Bereich seines axial vorderen und hinteren Endes sowie ggf. im mittleren Bereich an dem Dichtungsträger (20) anliegt. Infolge der kleinen Anlageflächen und des radialen Abstandes zum Dichtungsträger (20) wirken die Elemente (26, 28) als thermisch isolierende Abschirmung zwischen dem heißen Dichtungsträger (20) und dem luftgekühlten Gehäuse (10). Der Dichtungsträger weist an seinem stromaufwärtigen Ende einen hakenartigen Fortsatz auf, mit dem er das radial äußere Ende mindestens einer Leitschaufel (12) formschlüssig hält. Nachteilig dabei ist, dass der hakenartige Fortsatz den Heißgasen ausgesetzt ist, so dass mit Verschleiß,US-A-4,242,042 protects a gap maintaining system for gas turbines in which cooling air is guided longitudinally on the inside of a turbine housing (10), in particular a low-pressure turbine. The cooling air flow moves radially outward of the vanes and outside of the shrouds (14) surrounding shrouds. The segments of the shroud rings each comprise two functional elements, namely a seal carrier (20) provided with an inlet lining and a further bowl-like element (26, 28), which only in the region of its axially front and rear end and optionally in the middle region on the seal carrier (20) is present. Due to the small contact surfaces and the radial distance to the seal carrier (20), the elements (26, 28) act as a thermally insulating shield between the hot seal carrier (20) and the air-cooled housing (10). The seal carrier has at its upstream end a hook-like extension, with which it holds the radially outer end of at least one guide vane (12) in a form-fitting manner. The disadvantage here is that the hook-like extension is exposed to the hot gases, so that with wear,

Deformation und schlimmstenfalls Bruch zu rechnen ist. Es sei noch erwähnt, dass zwischen dem Turbinengehäuse (10) und den Elementen (26, 28) Federn (22, 24) angeordnet sind, welche die Mantelringsegmente radial nach Innen auf Anschlag halten.Deformation and, in the worst case, breakage is to be expected. It should be noted that between the turbine housing (10) and the elements (26, 28) springs (22, 24) are arranged, which hold the shroud segments radially inwardly to stop.

Demgegenüber besteht die Aufgabe der Erfindung darin, bei einer Gasturbine mit den Merkmalen des Oberbegriffs des Patentanspruches 1 einen segmentierten Mantelring mit Dichtungsträgerfunktion und Leitschaufelsicherungsfunktion so zu gestalten, dass durch thermische Entlastung der Leitschaufelbefestigungsstellen und des Turbinengehäuses die mechanische Belastbarkeit erhöht und somit Verschleiß und plastische Deformationen stark reduziert bzw. vermieden werden. Dabei soll insbesondere die Leitschaufelsicherungsfunktion mit höchster Zuverlässigkeit erfüllt werden.In contrast, the object of the invention is to make in a gas turbine with the features of the preamble of claim 1 a segmented shroud with seal carrier function and Leitschaufelsicherungsfunktion so that increases thermal stress relief of the Leitschaufelbefestigungsstellen and the turbine housing mechanical strength and thus wear and plastic deformation strong be reduced or avoided. In particular, the vane securing function should be met with the highest reliability.

Diese Aufgabe wird durch die in Patentanspruch 1 gekennzeichneten Merkmale gelöst, in Verbindung mit den gattungsbildenden Merkmalen in dessen Oberbegriff. Dabei werden die Dichtungsträgerfunktion einerseits und die Leitschaufelsicherungsfunktion andererseits jeweils von einem separaten Bauteil erfüllt, so dass jedes Segment des Mantelringes einen Dichtungsträger und ein Sicherungselement umfasst. Die Bauteile "Dichtungsträger" und "Sicherungselement" berühren sich, sie sind aber nicht fest miteinander verbunden. Der Dichtungsträger und das Sicherungselement sind in Relation zueinander so gestaltet, dass sie über möglichst große Bereiche ihrer Oberflächen voneinander beabstandet sind, sowie nur möglichst kleine gemeinsame, wärmeleitende Kontaktstellen aufweisen. Der Dichtungsträger nimmt im Betrieb annähernd die örtliche Heißgastemperatur an, wohingegen das Sicherungselement durch die abschirmende Wirkung des Dichtungsträgers bei minimierter Wärmeleitung auf deutlich niedrigerer Temperatur bleibt. Die gehäuseseitigen Leitschaufel-Befestigungselemente bleiben dadurch im Betrieb auch deutlich kühler und sind mechanisch erheblich höher belastbar. Die Temperaturreduktion setzt sich bis in das Turbinengehäuse hinein fort, wobei auch die abschirmende Wirkung des schalenartigen Sicherungselementes zum Tragen kommt. Zusätzliche Wärmeisolationsmaßnahmen bzw. -materialien sind dadurch in der Regel nicht mehr erforderlich. Dadurch, dass sich das Sicherungselement axial direkt am Gehäuse abstützt, bleibt die Leitschaufelsicherungsfunktion unabhängig von thermischen Dehnungen der nachfolgenden Leitschaufel im gesamten Betriebsbereich zuverlässig erfüllt.This object is achieved by the features characterized in claim 1 features, in conjunction with the generic features in the preamble. The seal carrier function on the one hand and the guide blade safety function on the other hand are each fulfilled by a separate component, so that each segment of the jacket ring comprises a seal carrier and a securing element. The components "seal carrier" and "fuse element" touch, but they are not firmly connected. The seal carrier and the securing element are designed in relation to each other so that they as possible large areas of their surfaces are spaced apart, and have only the smallest possible common, heat-conducting contact points. During operation, the seal carrier approximately assumes the local hot gas temperature, whereas the securing element remains at a significantly lower temperature due to the shielding effect of the seal carrier with minimized heat conduction. The housing-side guide vane fastening elements thereby remain significantly cooler during operation and are mechanically considerably higher load capacity. The temperature reduction continues into the turbine housing, whereby the shielding effect of the shell-like securing element also comes into play. Additional heat insulation measures or materials are therefore generally no longer required. Due to the fact that the securing element is supported axially directly on the housing, the guide blade safety function reliably remains independent of thermal expansions of the subsequent guide blade over the entire operating range.

Vorteilhafte Ausgestaltungen des Erfindungsgegenstandes sind in den Unteransprüchen gekennzeichnet.Advantageous embodiments of the subject invention are characterized in the subclaims.

Die Erfindung wird anschließend anhand der Zeichnung noch näher erläutert. Dabei zeigt die Figur einen Teillängsschnitt durch den äußeren Schaufelabdichtungs- und Gehäusebereich einer Niederdruckturbine eines Turboluftstrahltriebwerkes in vereinfachter Darstellung.The invention will be explained in more detail with reference to the drawing. The figure shows a partial longitudinal section through the outer Schaufelabdichtungs- and housing portion of a low-pressure turbine of a turbojet engine in a simplified representation.

Bei dem aus der Figur ersichtlichen Turbinenbereich handelt es sich um den Niederdruckturbinen- bzw. Nutzturbinenbereich, letzteres im Falle einer Wellenleistungsgasturbine. Bei Dreiwellen-Triebwerken könnte es sich auch um den Mitteldruckturbinenbereich handeln. Die Strömungsrichtung soll hier von links nach rechts veriaufen, wobei die gehäuseseitige Kanalbegrenzung divergent von links unten nach rechts oben ansteigt. Die Längsmittelachse/Rotationsachse der Gasturbine würde horizontal sowie unterhalb des Bildbereiches verlaufen, der Nabenbereich liegt ebenfalls zu tief, um von der Darstellung erfasst zu werden.The turbine region shown in the figure is the low-pressure turbine or useful turbine region, the latter in the case of a shaft power gas turbine. Three-shaft engines could also be the mid-pressure turbine area. The flow direction should run from left to right here, with the housing-side channel boundary rising divergently from bottom left to top right. The longitudinal center axis / rotation axis of the gas turbine would run horizontally and below the image area, the hub area is also too deep to be detected by the representation.

Die Erfindung betrifft konkret die konstruktive Ausführung der Laufschaufel-Spitzenabdichtung, d.h. der sogenannten Outer Air Seals (OAS). Der abzudichtende Laufschaufelkranz 11 weist ein Deckband 12 mit zwei Dichtspitzen 13,14 auf, welche mit einem hier im Durchmesser gestuften Einlaufbelag 6 in Honigwabenstruktur zusammenwirken. Stromaufwärts und stromabwärts des Laufschaufelkranzes 11 sind Leitschaufeln 15,16 zu erkennen, welche als Einzelteile oder als aus mehreren Schaufeln zusammengefasste Segmente statisch im Gehäuse 17 der Turbine angeordnet sind. Das radial äußere, stromabwärtige Ende der Leitschaufel 15 - oder des Leitschaufelsegmentes - liegt in einer radial nach innen offenen, rund um das Gehäuse 17 verlaufenden Nut 18. Das radial äußere, stromaufwärtige Ende der Leitschaufel 16 - oder des Leitschaufelsegmentes - greift in eine axial nach hinten offene, rund um das Gehäuse 17 verlaufende Nut 19. Eine vergleichbare, stromaufwärtige Aufhängung besitzt auch die Leitschaufel 15 (links außerhalb der Darstellung). Man kann sich vorstellen, dass die Leitschaufel 15, ohne weitere Sicherungsmaßnahmen im Gehäuse - und Nabenbereich, um ihre stromaufwärtige Aufhängung (siehe Bereich um Pos. 19) als "Gelenk" schwenkend aus der Nut 18 durch radiale Bewegung nach innen freikommen könnte. Hier setzt die Halte- und Sicherungsfunktion des Mantelringes 1 ein, der sich axial von der Leitschaufel 15 bis zur Leitschaufel 16 sowie in Umfangsrichtung rund um das Gehäuse 17 erstreckt. Es ist Stand der Technik, Mantelringe segmentiert auszuführen, es ist jedoch eine Besonderheit der vorliegenden Erfindung, die Segmente 2 in weitere Bauteile mit definierten Funktionen zu untergliedern. Heißgasseitig ist hier ein Dichtungsträger 3 angeordnet, der den Einlaufbelag 6 als Teil der Outer Air Seal (OAS) hält. Gehäuseseitig ist hier ein Sicherungselement 7 vorhanden, das in seiner primären Funktion die Leitschaufel 15 gegen Freikommen aus der Nut 18 sichert. Der Dichtungsträger 3 umfasst hier, neben dem Einlaufbelag 6, ein schalenartiges Trägerteil 4 und ein - im Axialschnitt -hakenähnliches Anschlagteil 5. Da mehrere solcher Dichtungsträger 3 über den Turbinenumfang aneinandergrenzend positioniert sind, können an diesen zusätzliche Abdichtungselemente, wie Zungen, Laschen etc. vorhanden sein. Diese sind jedoch nicht Teil der Erfindung und deshalb nicht dargestellt. Der Dichtungsträger 3 ist axial in gewissen Grenzen beweglich, wobei hier die vorderste Position mit wirksamem Anschlagteil 5 dargestellt ist. Da die dichtungstechnisch wirksamen Innenkonturen des Einlaufbelages 6 jeweils zylindrisch und axial ausreichend lang sind, ist die Axialposition nicht kritisch. Das Sicherungselement 7 umfasst ein im Axialschnitt C-förmiges Sicherungsteil 8, welches die Nut 18 mit dem Leitschaufelende untergreift, ein schalenartiges Abschirmteil 9 und ein im Axialschnitt hakenähnliches Anschlagteil 10. Die weitestgehend voneinander beabstandeten Elemente 3 und 7 weisen definierte Kontaktstellen C1, C2 auf, deren Erstreckung im Hinblick auf geringe Wärmeleitung minimiert ist, z.B. durch periodische Unterbrechungen in Umfangsrichtung, die jedoch für die gegenseitige Abstützung erforderlich sind. Es wäre denkbar, bei C1 und C2 lokale keramische Beschichtungen aufzubringen, um Verschleiß und Wärmeleitung weiter zu reduzieren. Das Sicherungselement 7 wirkt thermisch als zusätzliches Strahlungsschild zwischen dem heißen Dichtungsträger 3 und dem Gehäuse 17. Dadurch kann auf zusätzliche Wärmedämmstoffe in diesem Bereich verzichtet werden. Es ist auch zu erkennen, dass das heiße Trägerteil 4 erfindungsgemäß nicht direkt an den Befestigungselementen des Gehäuses 17 im Bereich der Nuten 18 und 19 anliegt. Somit werden diese mechanisch kritischen Bereiche ebenfalls thermisch entlastet. In diesem Zusammenhang ist es möglich, nur das Teil 4 aus thermischen Gründen aus einer Kobaltlegierung herzustellen, die Teile 5,6,8,9 und 10 können aus fertigungs- und verschleißtechnisch gutmütigeren Nickellegierungen oder sogar Stählen bestehen. Für feste Verbindungen innerhalb der Teile 3 und 7 ist ausschließlich Löten vorgesehen unter Verwendung geeigneter Hochtemperaturlote. Der Dichtungsträger 3 und/oder das Sicherungselement 7 kann aber auch jeweils integral als Drehteil aus einem Schmiedering oder als Gussteil hergestellt sein. Aufgrund der segmentierten Bauweise des Mantelringes 1 stellen die Teile 3 und 7 selbst Segmente dar, welche jeweils in größerer Zahl über den Gehäuseumfang aneinandergereiht sind. Dabei kann es sinnvoll sein, die Stoßfugen der Teile 7 gegenüber denjenigen der Teile 3 in Umfangsrichtung zu versetzen.The invention specifically relates to the structural design of the rotor blade tip seal, ie, the so-called O uter A ir S EFSA (OAS). The sealed blade ring 11 has a shroud 12 with two sealing tips 13,14, which cooperate with a here in the diameter stepped inlet lining 6 in honeycomb structure. Upstream and downstream of the blade ring 11 guide vanes 15,16 can be seen, which are statically arranged in the housing 17 of the turbine as individual parts or as combined from several blades segments. The radially outer, downstream end of the vane 15 - or the vane segment - lies in a radially inwardly open, around the housing 17 extending groove 18. The radially outer, upstream end of the vane 16 - or the vane segment - engages in an axial Rear open, running around the housing 17 groove 19. A similar, upstream suspension also has the vane 15 (left outside of the illustration). It can be envisaged that the vane 15, without further securing measures in the housing and hub region, could release its upstream suspension (see area at pos. 19) as a "hinge" pivoting out of the groove 18 by radial movement inwards. Here is the holding and securing function of the shroud 1, which extends axially from the vane 15 to the vane 16 and in the circumferential direction around the housing 17. It is state of the art, segmented perform coat rings, but it is a peculiarity of the present invention to subdivide the segments 2 into other components with defined functions. On the hot gas side, a seal carrier 3 is arranged here, which holds the inlet lining 6 as part of the outer air seal (OAS). On the housing side, a securing element 7 is present here, which secures the guide blade 15 against coming out of the groove 18 in its primary function. The seal carrier 3 comprises here, in addition to the inlet lining 6, a shell-like support member 4 and a - in the axial section hook-like stop member 5. Since several such seal carrier 3 are positioned adjacent to each other over the turbine circumference, on this additional sealing elements, such as tongues, tabs etc. available be. However, these are not part of the invention and therefore not shown. The seal carrier 3 is axially movable within certain limits, in which case the foremost position is shown with effective stop member 5. Since the sealing technically effective inner contours of the inlet lining 6 are each cylindrical and axially long enough, the axial position not critical. The securing element 7 comprises an axial section C-shaped securing part 8, which engages under the groove 18 with the guide blade end, a shell-like shielding part 9 and a hook-like in axial section stop member 10. The largely spaced elements 3 and 7 have defined contact points C1, C2, their extent is minimized in terms of low heat conduction, for example by periodic interruptions in the circumferential direction, which are required for mutual support. It would be conceivable to apply local ceramic coatings to C1 and C2 in order to further reduce wear and heat conduction. The fuse element 7 acts thermally as an additional radiation shield between the hot seal carrier 3 and the housing 17. This can be dispensed with additional heat insulation in this area. It can also be seen that the hot carrier part 4 according to the invention does not bear directly on the fastening elements of the housing 17 in the region of the grooves 18 and 19. Thus, these mechanically critical areas are also thermally relieved. In this connection, it is possible to produce only the part 4 for thermal reasons from a cobalt alloy, the parts 5,6,8,9 and 10 may consist of manufacturing and wear technically good-natured nickel alloys or even steels. For fixed connections within parts 3 and 7, brazing is provided exclusively using suitable high-temperature solders. However, the seal carrier 3 and / or the securing element 7 can also each be produced integrally as a turned part from a forged ring or as a cast part. Due to the segmented design of the shroud 1, the parts 3 and 7 themselves represent segments, which are juxtaposed in larger numbers over the housing circumference. It may be useful to move the butt joints of the parts 7 relative to those of the parts 3 in the circumferential direction.

Die Erfindung setzt nicht voraus, dass stromabwärts des Mantelringes ein Leitschaufelkranz folgt, wie in der Figur dargestellt. Es kann z.B. auch ein Gehäuseliner die konstruktive und strömungstechnische Fortsetzung des Mantelringes mit Abstützungs- und Anschlagfunktion für letzteren bilden.The invention does not assume that a vane ring follows downstream of the shell ring, as shown in the figure. It can e.g. Also a Gehäuseliner the constructive and fluidic continuation of the shroud with support and stop function for the latter form.

Claims (8)

  1. Gas turbine with a casing (17), with an axial through-flow low-pressure zone and/or working turbine zone, with at least one rotor blade ring (11) having a cover band (12) and with guide vanes (15) in the low-pressure and/or working turbine zone and with at least one shroud ring (1), which consists of several segments (2) arranged one after the other in the circumferential direction, which are positioned outside the rotor blade ring (11) with its cover band (12) and inside the casing (17) of the gas turbine, said segments having a running-in lining (6) for at least one sealing tip (13, 14) of the cover band (12) and holding the guide vanes (15) arranged upstream from the rotor blade ring (11) by positive locking at their radially outer, downstream end, such that each segment (2) comprises a seal support (3) on the hot gas side provided with the running-in lining (6) and a securing element (7) on the casing side which extends axially over a width comparable to the seal support (3), and such that the seal support (3) and the securing element (7) are spaced apart from one another over a large proportion of their surfaces and therefore have only small mutual heat-conducting contact points (C1, C2), characterised in that the securing element (7) holds at least one upstream guide vane and is supported axially directly against the casing (17) of the gas turbine by an abutment piece (10).
  2. Gas turbine according to Claim 1, characterised in that the running-in lining (6) is made as a honeycomb structure open towards the cover band (12) of the rotor blade ring (11) and is brazed to the seal support (3).
  3. Gas turbine according to Claims 1 or 2, characterised in that the securing element (7) comprises a securing portion (8) which is C-shaped in axial section, a shell-like screening portion (9) and an abutment piece (10) which is hook-shaped in axial section, these portions being brazed together.
  4. Gas turbine according to any of Claims 1 to 3, characterised in that the seal support (3) comprises a shell-like supporting portion (4), an abutment portion (5) which is hook-shaped in axial section and the running-in lining (6), these portions being brazed together.
  5. Gas turbine according to any of Claims 1 to 4, characterised in that the supporting portion (4) of the seal support (3) has points of mutual contact (C1, C2) with the securing portion (8) and with the downstream end of the screening portion (9) of the securing element (7).
  6. Gas turbine according to any of Claims 1 to 5, characterised in that each of the portions (3 to 10) of the shroud ring (1) consists of an alloy based on Fe, Ni or Co.
  7. Gas turbine according to Claim 6, characterised in that the supporting portion (4) consists of a Co-based alloy and the running-in lining (6), the securing portion (8), the screening portion (9) and the abutment portions (5, 10) consist in each case of a Ni-based alloy.
  8. Gas turbine according to Claims 1, 5 or 6, characterised in that the seal support (3) and/or the securing element (7) are each made integrally as a turned or cast component.
EP02729832A 2001-05-09 2002-03-28 Gas Turbine Expired - Lifetime EP1389265B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10122464A DE10122464C1 (en) 2001-05-09 2001-05-09 Mantle ring for low pressure turbine stage of gas turbine uses segments each having seal carrier and relatively spaced security element with minimum contact between them
DE10122464 2001-05-09
PCT/DE2002/001150 WO2002090724A1 (en) 2001-05-09 2002-03-28 Casing ring

Publications (2)

Publication Number Publication Date
EP1389265A1 EP1389265A1 (en) 2004-02-18
EP1389265B1 true EP1389265B1 (en) 2007-02-21

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EP02729832A Expired - Lifetime EP1389265B1 (en) 2001-05-09 2002-03-28 Gas Turbine

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US (1) US6966752B2 (en)
EP (1) EP1389265B1 (en)
DE (2) DE10122464C1 (en)
WO (1) WO2002090724A1 (en)

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Also Published As

Publication number Publication date
DE10122464C1 (en) 2002-03-07
US6966752B2 (en) 2005-11-22
DE50209543D1 (en) 2007-04-05
EP1389265A1 (en) 2004-02-18
WO2002090724A1 (en) 2002-11-14
US20040213666A1 (en) 2004-10-28

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