EP3022395A1 - Insert element, annular segment, gas turbine and mounting method - Google Patents

Insert element, annular segment, gas turbine and mounting method

Info

Publication number
EP3022395A1
EP3022395A1 EP14758840.4A EP14758840A EP3022395A1 EP 3022395 A1 EP3022395 A1 EP 3022395A1 EP 14758840 A EP14758840 A EP 14758840A EP 3022395 A1 EP3022395 A1 EP 3022395A1
Authority
EP
European Patent Office
Prior art keywords
insert element
ring segment
segment body
gas turbine
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14758840.4A
Other languages
German (de)
French (fr)
Other versions
EP3022395B1 (en
Inventor
Fathi Ahmad
Michael HÄNDLER
Kevin KAMPKA
Christian Kowalski
Christian Kowalzik
Nihal Kurt
Stefan Schmitt
Peter Schröder
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP14758840.4A priority Critical patent/EP3022395B1/en
Publication of EP3022395A1 publication Critical patent/EP3022395A1/en
Application granted granted Critical
Publication of EP3022395B1 publication Critical patent/EP3022395B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor

Definitions

  • the present invention relates to an insert member, a ring segment of a turbine of a gas turbine and a Gastur ⁇ bine and an assembly method. It is known and widely used that blade rows of turbines of gas turbines at the upper end of the blades have a so-called shroud.
  • Outer surface, an upstream flange and a downstream flange comprises.
  • the flanges hold the shroud ⁇ ring in a motor housing.
  • a perforateddovitzauf- is disposed on the flapper outer surface of the shroud ring Zvi ⁇ rule the upstream and the downstream flange, with a between the baffle plate and the outer surface ⁇ defined impingement chamber.
  • Axial cooling holes in the ring segment extend between the baffle and an outlet.
  • a trough adjacent the outlet directs cooling air from the outlet toward a downstream vane to cool the vane.
  • EP 0 132 182 A1 shows a sealing device for rotor blades of a turbomachine.
  • the sealing device comprises sectional seals. These are on the one hand fastened by means of connecting elements to an inner ring and attached to the other by hooks on an outer ring.
  • the inner ring has a low thermal inertia and the outer ring has an increased thermal inertia.
  • the section seals also have support ribs on the hooks and centering means.
  • GB 2206651 A shows a turbine blade shroud Banda North ⁇ voltage, which surrounds, in use, the ends of a stage of turbine blades in a gas turbine engine.
  • the shroud assembly includes a freely held in axial and radial direction of the ring on a fixed engine structure, a turbine blade shroud with a plurality of laterally abutting segments, each of which is hung on a radial side of the ring on ⁇ and positioned in a gas seal and has a relatively movable relative to the fixed engine structure, wherein the ring is formed of a material having a slower thermal response characteristic than the material of the solid engine structure.
  • EP 2 458 152 A2 discloses an axial flow type gas turbine comprising a rotor having alternating rows of air cooled blades and rotor heat shields, and a stator having alternating rows of air cooled vanes and stator heat shields mounted on inner rings.
  • the stator coaxially surrounds the rotor so that a hot gas path is defined between the stator and the rotor.
  • the rows of blades and stator heat shields, or rows of vanes and rotor heat shields, are located opposite each other.
  • a series of vanes and the following row of blades in the downstream direction define a turbine stage.
  • the blades are provided with outer blade platforms at their tips.
  • the blade platforms comprise on their outside a plurality of teeth which are arranged parallel to each other in the circumferential direction duri ⁇ fen and one behind the other in reasonable direction of the hot gas flow.
  • the present invention has for its object to overcome these disadvantages and to provide an insert element, a ring segment, a gas turbine and a mounting method, so that it is possible to operate a blade row without cover tape in the gas turbine.
  • the insert element according to the invention for attachment to a ring segment body of a turbine of a gas turbine is designed to cover a recess. It has a concave-shaped front side and a rear side with at least one shaping for positioning on the ring segment body.
  • the recess is arranged on a hot gas side of the Ringseg ⁇ ment body.
  • the ring segment body is characterized for operation with a shroud having run show ⁇ fel Herbert formed.
  • the insert element has at least one channel extending from the front side to an upper side.
  • the insert element can be fastened to the ring segment body in a simple manner with corresponding screws or bolts.
  • the insert element at least Coaxial with the channel arranged countersink on the front
  • the fastening means in particular the head of a screw, can thereby be sunk in the contour of the insert element.
  • the insert element has an upper molding and a lower molding.
  • the formations serve for a simpler, faster and more accurate positioning of the insert element before a fastening of the insert element to the ring segment body.
  • the assembly is thus simplified and possible with less effort.
  • the ring segment according to the invention of a turbine of a gas turbine ⁇ bine comprises a ring segment body with a in the assembled state a hot gas path facing hot gas side.
  • the ring segment body has a recess on the hot gas side.
  • an insert element of the type described above In particular, the insert element is screwed to the ring segment body.
  • the ring segment is thus designed for operation of a running show ⁇ fel Herbert having no shroud.
  • the gas turbine according to the invention comprises a turbine with a blade row and a ring formed from a plurality of ring segments, which is angeord ⁇ net around the blade row around. At least one of the ring segments is a ring ⁇ segment of the type described above.
  • a gas turbine which is ge ⁇ is suitable for operation with a rotor blade row without a shroud.
  • the upper housing of the gas turbine need not be lifted (cover lift). An access from the outlet side is sufficient.
  • the Gas turbine according to the invention is thus particularly suitable for experimental purposes, in which changes to the blades are made more frequently. With the present gas turbine these experiments could be constructed and carried out much faster.
  • gas turbine according to the invention can be equipped in a simple manner for operation with a blade row with shroud ⁇ by the at least one insert element is removed from the ring segment body.
  • an insert element is attached to a recess of a ring segment body of a turbine of a gas turbine.
  • the recess is disposed at a hot-gas side, which is supplied ⁇ Wandt in the assembled state of the ring segment body a hot gas path of the gas turbine.
  • the insert element is spent in the assembled state of the ring segment body in the hot gas path and then attached to the ring segment body.
  • the insert element is screwed, for example.
  • FIG. 1 shows a gas turbine according to the invention
  • FIG. 2 shows a ring segment according to the invention
  • FIG. 3 shows an insert element according to the invention.
  • 1 shows a gas turbine 10 according to the invention is sketched in an exemplary embodiment.
  • the gas turbine 10 includes a turbine 11 in which is disposed at least one running show ⁇ fel Herbert 12th Around this blade row 12 around a ring of a plurality of ring segments is arranged.
  • the blade row 12 is arranged rotatably about a rotation axis 20.
  • the blade row 12 is particularly the one located downstream of the other blade rows.
  • the corresponding blade row 12 is the fourth blade row of the turbine 11 of the gas turbine 10.
  • the gas turbine 10 according to the invention has at least one ring segment 13 according to the invention.
  • a ring segment 13 is sketched in an exemplary embodiment.
  • the ring segment 13 comprises a ring segment body 25 and an insert element 14.
  • the ring segment body 25 includes a hot gas side 27.
  • the hot gas side 27 is directed in the assembled state to a hot gas ⁇ path 26 of the gas turbine 10.
  • the insert element 14 covers a recess 23 in the ring ⁇ segment body 25 from.
  • the recess is arranged on the hot gas side 27.
  • This recess 23 has the ring segment ⁇ body 25 for the operation of the gas turbine 10 with a blade row, which has a shroud.
  • 12 contact the blade row without a shroud to ver ⁇ .
  • the ring segment body 25 can be adapted to the blade row 12, which has no shroud.
  • the adjustment is made by an inventive assembly method in which the insert member 14 is attached to the recess 23. In particular, this can be done while the ring segment body 25 is already mounted in the gas turbine 10. For this, the insert member 14 is brought into the hot gas path 26 and then introduced ⁇ is on the ring segment bodies 25th
  • FIG. 3 shows the insert element 14 in an exemplary embodiment.
  • the insert member 14 shown in a single view includes a concave-shaped ⁇ Before the side 15 and a rear side 16.
  • the front side 15 facing the hot gas path 26 in the assembled state.
  • the insert element 14 at least one mung Ausfor- 17, 18 for positioning on the ring segment body 25.
  • the insert element 14 comprises an upper molding 17 and two lower moldings 18. With the lower moldings 18, the insert element 14 can be pushed into an undercut 24 of the annular segment body 25 in a first assembly step M1. Subsequently, the insert element 14 can be folded in a second assembly step M2 to the ring segment body 25. With the upper Ausfor- mung 17 the insert element 14 is then positioned in its mounting Posi ⁇ tion. The insert element 14 shown has two channels 21 extending from the front side 15 to an upper side 22. In a third assembly step M3, the insert element 14 can now be screwed to the ring segment body 25. The means for screwing are guided through the channels 21. The insert element 14 is firmly connected to the ring segment body 25 after only three assembly steps.
  • the insert member 14 includes in montier ⁇ system state is preferably flush with the ring segment. 13 By mounting the insert element 14 on the ring segment body 25, an inventive ring segment 13 is produced.
  • the front side 15 of the insert element 14 according to the invention is designed to be concave and thus adapted to the ring segments 13 arranged around the blade row 12.
  • the illustrated insert element 14 has at the front side 15 in each case a countersink 19 per channel 21.
  • the cuts 19 are each ⁇ wells arranged coaxially to the channels 21st

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to an insert element (14) for fastening to a annular segment body (25) of a turbine (11) of a gas turbine (10). The annular segment body (25) has a recess (23) on a hot-gas side (27). The insert element (14) is designed to cover the recess (23) and has a concave front side (15) and a rear side (16) having at least one shaped portion (17, 18) for positioning on the annular segment body (25). The invention also relates to an annular segment (13) comprising the insert element (14), a gas turbine (10) comprising the insert element (14) and a mounting method for mounting the insert element (14).

Description

Beschreibung description
Einsatzelement, Ringsegment, Gasturbine, Montageverfahren Insert element, ring segment, gas turbine, assembly process
Die vorliegende Erfindung betrifft ein Einsatzelement, ein Ringsegment einer Turbine einer Gasturbine sowie eine Gastur¬ bine und ein Montageverfahren. Es ist bekannt und weit verbreitet, dass Laufschaufelreihen von Turbinen von Gasturbinen am oberen Ende der Schaufelblätter ein sogenanntes Deckband aufweisen. The present invention relates to an insert member, a ring segment of a turbine of a gas turbine and a Gastur ¬ bine and an assembly method. It is known and widely used that blade rows of turbines of gas turbines at the upper end of the blades have a so-called shroud.
Aus der US 2004/120803 AI ist ein gekühltes Turbinenkranzseg- ment für eine Gasturbine bekannt, welches ein axial verlau¬ fendes Deckbandringsegment mit einer Innenfläche, einer From US 2004/120803 Al a cooled Turbinenkranzseg- ment for a gas turbine is known, which has an axially duri ¬ fendes shroud ring segment with an inner surface, a
Außenfläche, einem stromaufwärtigen Flansch und einem stromabwärtigen Flansch umfasst. Die Flansche halten den Deckband¬ ring in einem Motorgehäuse. Eine perforierte Kühlluftauf- prallplatte ist auf der Außenfläche des Deckbandrings zwi¬ schen dem stromaufwärtigen und dem stromabwärtigen Flansch angeordnet, mit einer zwischen der Prallplatte und der Außen¬ fläche definierten Aufprallkammer . Axial verlaufende Kühlbohrungen in dem Ringsegment erstrecken sich zwischen der Prall- kammer und einem Auslass. Eine an den Auslass angrenzende Mulde leitet Kühlluft von dem Auslass in Richtung einer stromabwärtigen Leitschaufel, um die Leitschaufel zu kühlen. Outer surface, an upstream flange and a downstream flange comprises. The flanges hold the shroud ¬ ring in a motor housing. A perforated Kühlluftauf- is disposed on the flapper outer surface of the shroud ring Zvi ¬ rule the upstream and the downstream flange, with a between the baffle plate and the outer surface ¬ defined impingement chamber. Axial cooling holes in the ring segment extend between the baffle and an outlet. A trough adjacent the outlet directs cooling air from the outlet toward a downstream vane to cool the vane.
Die EP 0 132 182 AI zeigt eine Dichtungsvorrichtung für Lauf- schaufeln einer Turbomaschine. Die Dichtungsvorrichtung umfasst Abschnittsdichtungen. Diese sind zum einen mittels Verbindungselementen an einem Innenring befestigt und zum anderen durch Haken an einem Außenring befestigt. Der Innenring weist eine geringe Wärmeträgheit und der Außenring eine er- höhte Wärmeträgheit auf. Die Abschnittsdichtungen verfügen zudem über Stützrippen an den Haken und Zentriermittel. Die GB 2 206 651 A zeigt eine Turbinenschaufel Deckbandanord¬ nung, die im Gebrauch die Enden einer Stufe von Turbinenschaufeln in einem Gasturbinentriebwerk umgibt. Die Deckbandanordnung umfasst einen in axialer und radialer Richtung freigehaltenen Ring auf fester Triebwerkstruktur, ein Turbinenschaufeldeckband mit mehreren seitlich aneinanderstoßenden Segmenten, wobei jedes an einer radialen Seite des Rings auf¬ gehängt und in einer Gasabdichtung positioniert ist und ein relativ bewegliches Verhältnis zur festen Triebwerksstruktur aufweist, wobei der Ring aus einem Material gebildet ist, welches eine langsamere thermische Reaktionscharakteristik als das Material der festen Triebwerkstruktur aufweist. EP 0 132 182 A1 shows a sealing device for rotor blades of a turbomachine. The sealing device comprises sectional seals. These are on the one hand fastened by means of connecting elements to an inner ring and attached to the other by hooks on an outer ring. The inner ring has a low thermal inertia and the outer ring has an increased thermal inertia. The section seals also have support ribs on the hooks and centering means. GB 2206651 A shows a turbine blade shroud Banda North ¬ voltage, which surrounds, in use, the ends of a stage of turbine blades in a gas turbine engine. The shroud assembly includes a freely held in axial and radial direction of the ring on a fixed engine structure, a turbine blade shroud with a plurality of laterally abutting segments, each of which is hung on a radial side of the ring on ¬ and positioned in a gas seal and has a relatively movable relative to the fixed engine structure, wherein the ring is formed of a material having a slower thermal response characteristic than the material of the solid engine structure.
Die EP 2 458 152 A2 offenbart eine Gasturbine axialen Strö- mungstyps, welche einen Rotor mit alternierenden Reihen luftgekühlter Laufschaufeln und Rotorhitzeschilden, und einen Stator mit alternierenden Reihen luftgekühlter Leitschaufeln und Statorhitzeschilden, die auf Innenringen montiert sind, umfasst. Der Stator umgibt den Rotor koaxial, sodass zwischen Stator und Rotor ein Heißgaspfad definiert ist. Die Reihen der Laufschaufeln und der Statorhitzeschilde, beziehungsweise die Reihen der Leitschaufeln und der Rotorhitzeschilde sind sich gegenüber angeordnet. Eine Reihe von Leitschaufeln und die folgende Reihe von Laufschaufeln in stromabwärtiger Rich- tung definieren eine Turbinenstufe. Die Laufschaufeln sind mit äußeren Schaufelplattformen an ihren Spitzen versehen. Die Schaufelplattformen umfassen an ihrer Außenseite mehrere Zähne, welche parallel zueinander in Umfangsrichtung verlau¬ fen und hintereinander in Richtung des Heißgasflusses ange- ordnet sind. EP 2 458 152 A2 discloses an axial flow type gas turbine comprising a rotor having alternating rows of air cooled blades and rotor heat shields, and a stator having alternating rows of air cooled vanes and stator heat shields mounted on inner rings. The stator coaxially surrounds the rotor so that a hot gas path is defined between the stator and the rotor. The rows of blades and stator heat shields, or rows of vanes and rotor heat shields, are located opposite each other. A series of vanes and the following row of blades in the downstream direction define a turbine stage. The blades are provided with outer blade platforms at their tips. The blade platforms comprise on their outside a plurality of teeth which are arranged parallel to each other in the circumferential direction duri ¬ fen and one behind the other in reasonable direction of the hot gas flow.
Durch das Deckband ist es bei Eingriffen an der Laufschaufel¬ reihe, die beispielsweise zu Instandhaltungs- oder Erpro¬ bungszwecken erfolgen, notwendig, ein sogenanntes Cover-Lift, also ein Abheben des kompletten oberen Gehäuseteils, vorzu¬ nehmen. Ein Cover-Lift ist mit großem Aufwand verbunden. Der vorliegenden Erfindung liegt die Aufgabe zugrunde, diese Nachteile zu beheben und ein Einsatzelement, ein Ringsegment, eine Gasturbine sowie ein Montageverfahren bereitzustellen, sodass es möglich ist, auch eine Laufschaufelreihe ohne Deck- band in der Gasturbine zu betreiben. Through the shroud it is whenever acting on the blade ¬ series that take place for example for maintenance or Erpro ¬ advertising purposes, required a so-called cover-lift, so lifting the entire upper case, vorzu take ¬. A cover lift is associated with great effort. The present invention has for its object to overcome these disadvantages and to provide an insert element, a ring segment, a gas turbine and a mounting method, so that it is possible to operate a blade row without cover tape in the gas turbine.
Gelöst wird diese Aufgabe mit einem Einsatzelement nach An¬ spruch 1, einem Ringsegment nach Anspruch 5, einer Gasturbine nach Anspruch 7 sowie einem Montageverfahren nach Anspruch 8. Vorteilhafte Weiterbildungen der Erfindung sind in den Unteransprüchen angegeben und in der Beschreibung beschrieben. This object is achieved with an insert element according to ¬ claim 1., a ring segment of claim 5, a gas turbine according to claim 7, and an assembly method according to claim 8. Advantageous developments of the invention are specified in the sub-claims and described in the specification.
Das erfindungsgemäße Einsatzelement zur Befestigung an einem Ringsegmentkörper einer Turbine einer Gasturbine ist zur Ab- deckung einer Aussparung ausgebildet. Es weist eine konkav geformte Vorderseite und eine Rückseite mit zumindest einer Ausformung zur Positionierung an dem Ringsegmentkörper auf. Die Aussparung ist dabei an einer Heißgasseite des Ringseg¬ mentkörpers angeordnet. Der Ringsegmentkörper ist dadurch für einen Betrieb mit einer ein Deckband aufweisenden Laufschau¬ felreihe ausgebildet. The insert element according to the invention for attachment to a ring segment body of a turbine of a gas turbine is designed to cover a recess. It has a concave-shaped front side and a rear side with at least one shaping for positioning on the ring segment body. The recess is arranged on a hot gas side of the Ringseg ¬ ment body. The ring segment body is characterized for operation with a shroud having run show ¬ felreihe formed.
Mit dieser Anordnung ist es vorteilhaft ermöglicht eine Gas¬ turbine von einem Betrieb mit einer Laufschaufelreihe mit Deckband auf einen Betrieb mit einer Laufschaufelreihe ohneWith this arrangement, it is advantageous to allow a gas turbine ¬ from operation with a blade row with shroud to an operation with a rotor blade row without
Deckband umzurüsten. Eine wesentlich aufwändigere Neuanferti¬ gung eines passenden Ringsegments kann erspart bleiben. Convert the shroud. A much more elaborate Neuanferti ¬ supply a matching ring segment can be spared.
In einer vorteilhaften Ausgestaltung des erfindungsgemäßen Einsatzelements weist das Einsatzelement zumindest einen von der Vorderseite zu einer Oberseite verlaufenden Kanal auf. In an advantageous embodiment of the insert element according to the invention, the insert element has at least one channel extending from the front side to an upper side.
Damit kann das Einsatzelement mit entsprechenden Schrauben oder Bolzen in einfacher Weise an dem Ringsegmentkörper be- festigt werden. Thus, the insert element can be fastened to the ring segment body in a simple manner with corresponding screws or bolts.
In einer weiteren vorteilhaften Ausgestaltung des erfindungsgemäßen Einsatzelements weist das Einsatzelement zumindest koaxial zum Kanal angeordnete Senkung an der Vorderseite In a further advantageous embodiment of the insert element according to the invention, the insert element at least Coaxial with the channel arranged countersink on the front
Die Befestigungsmittel, insbesondere der Kopf einer Schraube, kann dadurch in der Kontur des Einsatzelements versenkt wer- The fastening means, in particular the head of a screw, can thereby be sunk in the contour of the insert element.
In einer weiteren vorteilhaften Ausgestaltung des erfindungsgemäßen Einsatzelements weist das Einsatzelement eine obere Ausformung und eine untere Ausformung auf. In a further advantageous embodiment of the insert element according to the invention, the insert element has an upper molding and a lower molding.
Die Ausformungen dienen einer einfacheren, schnelleren und genaueren Positionierung des Einsatzelements vor einem Befestigen des Einsatzelements an dem Ringsegmentkörper. Die Mon- tage ist dadurch vereinfacht und mit weniger Aufwand möglich. The formations serve for a simpler, faster and more accurate positioning of the insert element before a fastening of the insert element to the ring segment body. The assembly is thus simplified and possible with less effort.
Das erfindungsgemäße Ringsegment einer Turbine einer Gastur¬ bine umfasst einen Ringsegmentkörper mit einer in montiertem Zustand einem Heißgaspfad zugewandten Heißgasseite. Der Ring- segmentkörper weist an der Heißgasseite eine Aussparung auf. In der Aussparung ein Einsatzelement der zuvor beschriebenen Art angeordnet. Insbesondere ist das Einsatzelement mit dem Ringsegmentkörper verschraubt. Das Ringsegment ist damit für einen Betrieb einer Laufschau¬ felreihe ausgebildet, die kein Deckband aufweist. The ring segment according to the invention of a turbine of a gas turbine ¬ bine comprises a ring segment body with a in the assembled state a hot gas path facing hot gas side. The ring segment body has a recess on the hot gas side. In the recess arranged an insert element of the type described above. In particular, the insert element is screwed to the ring segment body. The ring segment is thus designed for operation of a running show ¬ felreihe having no shroud.
Die erfindungsgemäße Gasturbine umfasst eine Turbine mit einer Laufschaufelreihe und einem aus mehreren Ringsegmenten gebildeten Ring, der um die Laufschaufelreihe herum angeord¬ net ist. Zumindest eins der Ringsegmente ist dabei ein Ring¬ segment der zuvor beschriebenen Art. The gas turbine according to the invention comprises a turbine with a blade row and a ring formed from a plurality of ring segments, which is angeord ¬ net around the blade row around. At least one of the ring segments is a ring ¬ segment of the type described above.
Damit ist vorteilhaft eine Gasturbine bereitgestellt, die für einen Betrieb mit einer Laufschaufelreihe ohne Deckband ge¬ eignet ist. Bei einem Austausch der Laufschaufeln braucht nicht das obere Gehäuse der Gasturbine abgehoben zu werden (Cover-Lift) . Ein Zugang von der Auslassseite her genügt. Die erfindungsgemäße Gasturbine eignet sich damit insbesondere für Versuchszwecke, bei denen häufiger Änderungen an den Schaufelblättern vorgenommen werden. Mit der vorliegenden Gasturbine könne diese Versuche erheblich schneller aufgebaut und durchgeführt werden. Thus, a gas turbine is advantageously provided which is ge ¬ is suitable for operation with a rotor blade row without a shroud. When replacing the blades, the upper housing of the gas turbine need not be lifted (cover lift). An access from the outlet side is sufficient. The Gas turbine according to the invention is thus particularly suitable for experimental purposes, in which changes to the blades are made more frequently. With the present gas turbine these experiments could be constructed and carried out much faster.
Zudem kann die erfindungsgemäße Gasturbine in einfacher Weise für den Betrieb mit einer Laufschaufelreihe mit Deckband um¬ gerüstet werden, indem das zumindest eine Einsatzelement vom Ringsegmentkörper entfernt wird. In addition, the gas turbine according to the invention can be equipped in a simple manner for operation with a blade row with shroud ¬ by the at least one insert element is removed from the ring segment body.
Bei dem erfindungsgemäßen Montageverfahren wird ein Einsatzelement an einer Aussparung eines Ringsegmentkörpers einer Turbine einer Gasturbine angebracht. Die Aussparung ist dabei an einer Heißgasseite angeordnet, die in montiertem Zustand des Ringsegmentkörpers einem Heißgaspfad der Gasturbine zuge¬ wandt ist. Insbesondere wird das Einsatzelement im montierten Zustand des Ringsegmentkörpers in den Heißgaspfad verbracht und anschließend an den Ringsegmentkörper angebracht. Das Einsatzelement wird beispielsweise angeschraubt. In the assembly method according to the invention, an insert element is attached to a recess of a ring segment body of a turbine of a gas turbine. The recess is disposed at a hot-gas side, which is supplied ¬ Wandt in the assembled state of the ring segment body a hot gas path of the gas turbine. In particular, the insert element is spent in the assembled state of the ring segment body in the hot gas path and then attached to the ring segment body. The insert element is screwed, for example.
Damit kann ein Ringsegment einer Gasturbine insbesondere für Testzwecke mit geringem Aufwand von einer Auslegung für einen Betrieb mit einer Laufschaufelreihe mit Deckband in eine Aus- legung für einen Betrieb mit einer Laufschaufelreihe ohne Deckband umgerüstet werden. Auch ein Zurückbau ist leicht möglich . Thus, a ring segment of a gas turbine, in particular for test purposes with little effort from a design for operation with a blade row with shroud in an interpretation for operation with a blade row without shroud be converted. A dismantling is easily possible.
Ausführungsbeispiele der Erfindung werden anhand der Zeich- nungen und der nachfolgenden Beschreibung näher erläutert. Es zeigen : Embodiments of the invention will be explained in more detail with reference to the drawings and the description below. Show it :
Figur 1 eine erfindungsgemäße Gasturbine, Figur 2 ein erfindungsgemäßes Ringsegment, 1 shows a gas turbine according to the invention, FIG. 2 shows a ring segment according to the invention,
Figur 3 ein erfindungsgemäßes Einsatzelement. In der Figur 1 ist eine erfindungsgemäße Gasturbine 10 in einer beispielhaften Ausgestaltung skizziert. Die Gasturbine 10 umfasst eine Turbine 11 in der wenigstens eine Laufschau¬ felreihe 12 angeordnet ist. Um diese Laufschaufelreihe 12 herum ist ein Ring aus mehreren Ringsegmenten angeordnet. Die Laufschaufelreihe 12 ist um eine Rotationsachse 20 drehbar angeordnet . FIG. 3 shows an insert element according to the invention. 1 shows a gas turbine 10 according to the invention is sketched in an exemplary embodiment. The gas turbine 10 includes a turbine 11 in which is disposed at least one running show ¬ felreihe 12th Around this blade row 12 around a ring of a plurality of ring segments is arranged. The blade row 12 is arranged rotatably about a rotation axis 20.
Bei der Laufschaufelreihe 12 handelt es sich insbesondere um die stromabwärts der anderen Laufschaufelreihen gelegene. In der Figur 1 ist die entsprechende Laufschaufelreihe 12 die vierte Laufschaufelreihe der Turbine 11 der Gasturbine 10. The blade row 12 is particularly the one located downstream of the other blade rows. In FIG. 1, the corresponding blade row 12 is the fourth blade row of the turbine 11 of the gas turbine 10.
Die erfindungsgemäße Gasturbine 10 weist wenigstens ein er- findungsgemäßes Ringsegment 13 auf. In der Figur 2 ist ein Ringsegment 13 in einer beispielhaften Ausgestaltung skizziert . The gas turbine 10 according to the invention has at least one ring segment 13 according to the invention. In the figure 2, a ring segment 13 is sketched in an exemplary embodiment.
Das Ringsegment 13 umfasst einen Ringsegmentkörper 25 und ein Einsatzelement 14. The ring segment 13 comprises a ring segment body 25 and an insert element 14.
Der Ringsegmentkörper 25 umfasst eine Heißgasseite 27. Die Heißgasseite 27 ist in montiertem Zustand zu einem Heißgas¬ pfad 26 der Gasturbine 10 gerichtet. The ring segment body 25 includes a hot gas side 27. The hot gas side 27 is directed in the assembled state to a hot gas ¬ path 26 of the gas turbine 10.
Das Einsatzelement 14 deckt eine Aussparung 23 in dem Ring¬ segmentkörper 25 ab. Die Aussparung ist an der Heißgasseite 27 angeordnet. Diese Aussparung 23 besitzt der Ringsegment¬ körper 25 für den Betrieb der Gasturbine 10 mit einer Lauf- schaufelreihe, die ein Deckband aufweist. Um beispielsweise in einer Erprobungsphase nicht die gesamte obere Gehäuse¬ hälfte der Gasturbine abnehmen zu müssen (Cover-Lift) ist es vorteilhaft, die Laufschaufelreihe 12 ohne Deckband zu ver¬ wenden. Mittels des erfindungsgemäßen Einsatzelements 14 kann der Ringsegmentkörper 25 an die Laufschaufelreihe 12, die kein Deckband aufweist, angepasst werden. Die Anpassung erfolgt durch ein erfindungsgemäßes Montageverfahren, bei dem das Einsatzelement 14 an der Aussparung 23 angebracht wird. Insbesondere kann dies erfolgen, während der Ringsegmentkörper 25 bereits in der Gasturbine 10 montiert ist. Dazu wird das Einsatzelement 14 in den Heißgaspfad 26 verbracht und anschließend an dem Ringsegmentkörper 25 ange¬ bracht . The insert element 14 covers a recess 23 in the ring ¬ segment body 25 from. The recess is arranged on the hot gas side 27. This recess 23 has the ring segment ¬ body 25 for the operation of the gas turbine 10 with a blade row, which has a shroud. For example, not having to remove the entire upper housing ¬ half of the gas turbine in a trial phase (cover-elevator), it is advantageous, 12 contact the blade row without a shroud to ver ¬. By means of the insert element 14 according to the invention, the ring segment body 25 can be adapted to the blade row 12, which has no shroud. The adjustment is made by an inventive assembly method in which the insert member 14 is attached to the recess 23. In particular, this can be done while the ring segment body 25 is already mounted in the gas turbine 10. For this, the insert member 14 is brought into the hot gas path 26 and then introduced ¬ is on the ring segment bodies 25th
In der Figur 3 ist das Einsatzelement 14 in einer beispiel- haften Ausgestaltung dargestellt. Das in einer Einzelansicht gezeigte Einsatzelement 14 umfasst eine konkav geformte Vor¬ derseite 15 und eine Rückseite 16. Die Vorderseite 15 ist im montierten Zustand dem Heißgaspfad 26 zugewandt. An der Rück¬ seite 16 weist das Einsatzelement 14 zumindest eine Ausfor- mung 17, 18 zur Positionierung an dem Ringsegmentkörper 25 auf . FIG. 3 shows the insert element 14 in an exemplary embodiment. The insert member 14 shown in a single view includes a concave-shaped ¬ Before the side 15 and a rear side 16. The front side 15 facing the hot gas path 26 in the assembled state. On the rear ¬ page 16, the insert element 14 at least one mung Ausfor- 17, 18 for positioning on the ring segment body 25.
In der gezeigten Ausgestaltung umfasst das Einsatzelement 14 eine obere Ausformung 17 und zwei untere Ausformungen 18. Mit den unteren Ausformungen 18 kann das Einsatzelement 14 in einem ersten Montageschritt Ml in einen Hinterschnitt 24 des Ringsegmentkörpers 25 geschoben werden. Anschließend kann das Einsatzelement 14 in einem zweiten Montageschritt M2 an den Ringsegmentkörper 25 geklappt werden. Mit der oberen Ausfor- mung 17 ist das Einsatzelement 14 dann in seiner Montageposi¬ tion positioniert. Das gezeigte Einsatzelement 14 weist zwei von der Vorderseite 15 zu einer Oberseite 22 verlaufende Kanäle 21 auf. In einem dritten Montageschritt M3 kann das Einsatzelement 14 nun mit dem Ringsegmentkörper 25 ver- schraubt werden. Die Mittel zum Verschrauben werden dabei durch die Kanäle 21 geführt. Das Einsatzelement 14 ist nach lediglich drei Montageschritten fest mit dem Ringsegmentkörper 25 verbunden. Das Einsatzelement 14 schließt in montier¬ tem Zustand bevorzugt bündig mit dem Ringsegment 13 ab. Durch die Montage des Einsatzelements 14 an dem Ringsegmentkörper 25 ist ein erfindungsgemäßes Ringsegment 13 hergestellt. Die Vorderseite 15 des erfindungsgemäßen Einsatzelements 14 ist konkav ausgeführt und damit den um die Laufschaufelreihe 12 herum angeordneten Ringsegmenten 13 angepasst. Das gezeigte Einsatzelement 14 weist an der Vorderseite 15 jeweils eine Senkung 19 je Kanal 21 auf. Die Senkungen 19 sind je¬ weils koaxial zu den Kanälen 21 angeordnet. In the embodiment shown, the insert element 14 comprises an upper molding 17 and two lower moldings 18. With the lower moldings 18, the insert element 14 can be pushed into an undercut 24 of the annular segment body 25 in a first assembly step M1. Subsequently, the insert element 14 can be folded in a second assembly step M2 to the ring segment body 25. With the upper Ausfor- mung 17 the insert element 14 is then positioned in its mounting Posi ¬ tion. The insert element 14 shown has two channels 21 extending from the front side 15 to an upper side 22. In a third assembly step M3, the insert element 14 can now be screwed to the ring segment body 25. The means for screwing are guided through the channels 21. The insert element 14 is firmly connected to the ring segment body 25 after only three assembly steps. The insert member 14 includes in montier ¬ system state is preferably flush with the ring segment. 13 By mounting the insert element 14 on the ring segment body 25, an inventive ring segment 13 is produced. The front side 15 of the insert element 14 according to the invention is designed to be concave and thus adapted to the ring segments 13 arranged around the blade row 12. The illustrated insert element 14 has at the front side 15 in each case a countersink 19 per channel 21. The cuts 19 are each ¬ weils arranged coaxially to the channels 21st
Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele einge¬ schränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen . Although the invention in detail by the preferred embodiment has been illustrated and described in detail, the invention is not limited ¬ by the disclosed examples and other variations can be derived therefrom by the skilled artisan without departing from the scope of the invention.

Claims

Patentansprüche claims
1. Einsatzelement (14) zur Befestigung an einem Ringseg- mentkörper (25) einer Turbine (11) einer Gasturbine (10), wobei der Ringsegmentkörper (25) an einer Heißgasseite (27) eine Aussparung (23) aufweist, 1. insert element (14) for attachment to a ring segment body (25) of a turbine (11) of a gas turbine (10), wherein the ring segment body (25) has a recess (23) on a hot gas side (27),
wobei das Einsatzelement (14) zur Abdeckung der Aussparung (23) ausgebildet ist und eine konkav geformte Vorderseite (15) und eine Rückseite (16) mit zumindest einer Ausformung wherein the insert element (14) is designed to cover the recess (23) and has a concave-shaped front side (15) and a rear side (16) with at least one molding
(17, 18) zur Positionierung an dem Ringsegmentkörper (25) aufweist . (17, 18) for positioning on the ring segment body (25).
2. Einsatzelement (14) nach Anspruch 1, 2. insert element (14) according to claim 1,
wobei das Einsatzelement (14) zumindest einen von der Vor¬ derseite (15) zu einer Oberseite (22) verlaufenden Kanal (21) aufweist. wherein said insert member (14) has at least one extending from the front of the side ¬ (15) to a top (22) channel (21).
3. Einsatzelement (14) nach Anspruch 1, 3. insert element (14) according to claim 1,
wobei das Einsatzelement (14) zumindest eine koaxial zum wherein the insert element (14) at least one coaxial with
Kanal (21) angeordnete Senkung (19) an der Vorderseite (15) aufweist . Channel (21) arranged reduction (19) on the front side (15).
4. Einsatzelement (14) nach einem der Ansprüche 1 bis 3, wobei das Einsatzelement (14) eine obere Ausformung (17) und eine untere Ausformung (18) aufweist. 4. insert element (14) according to one of claims 1 to 3, wherein the insert element (14) has an upper molding (17) and a lower molding (18).
5. Ringsegment (13) einer Turbine (11) einer Gasturbine 5. ring segment (13) of a turbine (11) of a gas turbine
(10) ,  (10),
wobei das Ringsegment einen Ringsegmentkörper (25) mit einer in montiertem Zustand einem Heißgaspfad (26) zu¬ gewandten Heißgasseite (27) umfasst, wherein the ring segment includes an annular segment body (25) having a mounted state in a hot gas path (26) ¬ facing hot-gas side (27),
wobei der Ringsegmentkörper (25) an der Heißgasseite (27) eine Aussparung (23) aufweist und in der Aussparung (23) ein Einsatzelement (14) nach einem der vorherigen Ansprüche angeordnet ist. wherein the ring segment body (25) on the hot gas side (27) has a recess (23) and in the recess (23) an insert element (14) is arranged according to one of the preceding claims.
6. Ringsegment (13) nach Anspruch 5, 6. ring segment (13) according to claim 5,
wobei das Einsatzelement (14) mit dem Ringsegmentkörper (25) verschraubt ist.  wherein the insert element (14) is screwed to the ring segment body (25).
7. Gasturbine (10) mit einer eine Laufschaufelreihe (12) aufweisenden Turbine (11) und einem aus mehreren Ringseg¬ menten gebildeten, um die Laufschaufelreihe (12) herum angeordneten Ring, 7. gas turbine (10) with a blade row (12) having a turbine (11) and formed of a plurality of Ringseg ¬ ments, around the blade row (12) arranged around ring,
wobei zumindest eins der Ringsegmente ein Ringsegment (13) nach Anspruch 5 oder 6 ist.  wherein at least one of the ring segments is a ring segment (13) according to claim 5 or 6.
8. Montageverfahren, bei dem ein Einsatzelement (14) an einer Aussparung (23) eines Ringsegmentkörpers (25) einer Turbine (11) einer Gasturbine (10) angebracht wird, 8. An assembly method in which an insert element (14) is attached to a recess (23) of a ring segment body (25) of a turbine (11) of a gas turbine (10),
wobei die Aussparung (23) an einer in montiertem Zustand des Ringsegmentkörpers (25) einem Heißgaspfad (26) der Gasturbine (10) zugewandten Heißgasseite (27) angeordnet ist .  wherein the recess (23) at a in the assembled state of the ring segment body (25) a hot gas path (26) of the gas turbine (10) facing the hot gas side (27) is arranged.
9. Montageverfahren nach Anspruch 8, 9. Mounting method according to claim 8,
wobei das Einsatzelement (14) im montierten Zustand des Ringsegmentkörpers (25) in den Heißgaspfad (26) verbracht wird und anschließend an den Ringsegmentkörper (25) ange¬ bracht wird. wherein the insert element (14) is brought in the assembled state of the ring segment body (25) in the hot gas path (26) and then attached to the ring segment body (25) is ¬ introduced .
10. Montageverfahren nach Anspruch 8 oder 9, 10. Mounting method according to claim 8 or 9,
wobei das Einsatzelement (14) an den Ringsegmentkörper (25) angeschraubt (M3) wird.  wherein the insert member (14) is screwed (M3) to the ring segment body (25).
EP14758840.4A 2013-09-25 2014-08-29 Insert element and gas turbine Not-in-force EP3022395B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14758840.4A EP3022395B1 (en) 2013-09-25 2014-08-29 Insert element and gas turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP13185947.2A EP2853685A1 (en) 2013-09-25 2013-09-25 Insert element and gas turbine
PCT/EP2014/068359 WO2015043876A1 (en) 2013-09-25 2014-08-29 Insert element, annular segment, gas turbine and mounting method
EP14758840.4A EP3022395B1 (en) 2013-09-25 2014-08-29 Insert element and gas turbine

Publications (2)

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EP3022395A1 true EP3022395A1 (en) 2016-05-25
EP3022395B1 EP3022395B1 (en) 2017-08-16

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JP (1) JP6227765B2 (en)
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DE102017205794A1 (en) 2017-04-05 2018-10-11 Siemens Aktiengesellschaft Method for sealing an annular gap in a turbine and turbine

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EP3022395B1 (en) 2017-08-16
CN105593470B (en) 2017-05-31
US20160201497A1 (en) 2016-07-14
EP2853685A1 (en) 2015-04-01
US10018051B2 (en) 2018-07-10
JP2016535188A (en) 2016-11-10
CN105593470A (en) 2016-05-18
WO2015043876A1 (en) 2015-04-02
JP6227765B2 (en) 2017-11-08

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