EP2853685A1 - Insert element and gas turbine - Google Patents

Insert element and gas turbine Download PDF

Info

Publication number
EP2853685A1
EP2853685A1 EP13185947.2A EP13185947A EP2853685A1 EP 2853685 A1 EP2853685 A1 EP 2853685A1 EP 13185947 A EP13185947 A EP 13185947A EP 2853685 A1 EP2853685 A1 EP 2853685A1
Authority
EP
European Patent Office
Prior art keywords
insert element
ring segment
gas turbine
shroud
blade row
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.)
Withdrawn
Application number
EP13185947.2A
Other languages
German (de)
French (fr)
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 EP13185947.2A priority Critical patent/EP2853685A1/en
Priority to CN201480052860.8A priority patent/CN105593470B/en
Priority to US15/023,391 priority patent/US10018051B2/en
Priority to JP2016516887A priority patent/JP6227765B2/en
Priority to EP14758840.4A priority patent/EP3022395B1/en
Priority to PCT/EP2014/068359 priority patent/WO2015043876A1/en
Publication of EP2853685A1 publication Critical patent/EP2853685A1/en
Withdrawn legal-status Critical Current

Links

Images

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 element for attachment to a ring segment of a turbine of a gas turbine, which is designed for operation with a shroud having a shroud row.
  • the present invention relates to a gas turbine.
  • cover-lift Due to the shroud, it is necessary to perform a so-called cover-lift, ie a lift-off of the complete upper housing part during interventions on the blade row, which are made for example for maintenance or testing purposes.
  • 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 with which it is possible to operate a blade row without shroud in the gas turbine.
  • the insert element according to the invention for fastening to a ring segment of a turbine of a gas turbine has a concave-shaped front side and a rear side with at least one shaping for positioning on the ring segment.
  • the ring segment is designed for operation with a shroud having a shroud row.
  • the insert element has at least one channel extending from the front side to an upper side.
  • the insert element can be fastened with appropriate screws or bolts in a simple manner to the ring segment.
  • the insert element has at least one coaxial with the channel arranged reduction on the front side.
  • 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 easier, faster and more accurate positioning of the insert element before securing the insert element to the ring segment.
  • the assembly is simplified and possible with less effort.
  • the insert element is preferably integrated in a gas turbine.
  • the gas turbine according to the invention comprises a turbine with a blade row and a ring segment arranged around the blade row.
  • the ring segment is for operation with a shroud row having a shroud educated.
  • the insert element is attached to the ring segment.
  • a gas turbine is advantageously provided which is suitable for operation with a blade row without 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 therefore particularly suitable for experimental purposes in which frequent changes to the blades are made. With the present gas turbine these experiments could be constructed and carried out much faster.
  • gas turbine according to the invention can be converted 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.
  • FIG. 1 a gas turbine 10 according to the invention is sketched in an exemplary embodiment.
  • the gas turbine 10 according to the invention comprises a turbine 11 in which at least one blade row 12 is arranged.
  • To this blade row 12 around a ring segment 13 is arranged according to the invention.
  • 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 fourth blade row of the turbine 11 of the gas turbine 10th is particularly the one located downstream of the other blade rows.
  • the gas turbine 10 has at least one insert element 14 fastened to the ring segment 13.
  • the arrangement of the insert member 14 in the ring segment is sketched in an exemplary embodiment in a sectional view.
  • the insert element 14 covers a recess 23 in the ring segment 13.
  • This recess 23 has the ring segment 13 for the operation of the gas turbine 10 with a blade row having a shroud.
  • the ring segment 13 can be adapted to the blade row 12, which has no shroud.
  • the insert element 14 shown in a single view comprises a concave front side 15 and a back side 16.
  • the insert element 14 according to the invention has at least one projection 17, 18 for positioning on the ring segment 13.
  • 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 13 in a first assembly step M1. Subsequently, the insert element 14 can be folded in a second assembly step M2 to the ring segment 13. With the upper molding 17, the insert member 14 is then positioned in its mounting position. The insert element 14 shown has two channels extending from the front side 15 to an upper side 22 21 on. In a third assembly step M3, the insert element 14 can now be screwed to the ring segment 13. The means for screwing are guided through the channels 21. The insert element 14 is firmly connected to the ring segment 13 after only three assembly steps. In the assembled state, the insert element 14 preferably ends flush with the ring segment 13.
  • the front side 15 of the insert element 14 according to the invention is designed to be concave and thus adapted to the ring segment 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 depressions 19 are each arranged coaxially with the channels 21.

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

Die Erfindung betrifft ein Einsatzelement (14) zur Befestigung an einem Ringsegment (13) einer Turbine (11) einer Gasturbine (10). Das Ringsegment (13) ist dabei für einen Betrieb mit einer ein Deckband aufweisenden Laufschaufelreihe ausgebildet. Das Einsatzelement (14) weist eine konkav geformte Vorderseite (15) und eine Rückseite (16) mit zumindest einer Ausformung (17, 18) zur Positionierung an dem Ringsegment (13) auf. Zudem wird eine Gasturbine (10) mit dem Einsatzelement (14) beansprucht.The invention relates to an insert element (14) for attachment to a ring segment (13) of a turbine (11) of a gas turbine (10). The ring segment (13) is designed for operation with a shroud having a shroud row. The insert element (14) has a concave-shaped front side (15) and a rear side (16) with at least one molding (17, 18) for positioning on the ring segment (13). In addition, a gas turbine (10) is claimed with the insert element (14).

Description

Die vorliegende Erfindung betrifft ein Einsatzelement zur Befestigung an einem Ringsegment einer Turbine einer Gasturbine, welches für einen Betrieb mit einer ein Deckband aufweisenden Laufschaufelreihe ausgebildet ist. Zudem betrifft die vorliegende Erfindung eine Gasturbine.The present invention relates to an insert element for attachment to a ring segment of a turbine of a gas turbine, which is designed for operation with a shroud having a shroud row. In addition, the present invention relates to a gas turbine.

Es ist bekannt und weit verbreitet, dass Laufschaufelreihen von Turbinen von Gasturbinen am oberen Ende der Schaufelblätter ein sogenanntes Deckband aufweisen.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.

Durch das Deckband ist es bei Eingriffen an der Laufschaufelreihe, die beispielsweise zu Instandhaltungs- oder Erprobungszwecken erfolgen, notwendig, ein sogenanntes Cover-Lift, also ein Abheben des kompletten oberen Gehäuseteils, vorzunehmen. Ein Cover-Lift ist mit großem Aufwand verbunden.Due to the shroud, it is necessary to perform a so-called cover-lift, ie a lift-off of the complete upper housing part during interventions on the blade row, which are made for example for maintenance or testing purposes. A cover lift is associated with great effort.

Der vorliegenden Erfindung liegt die Aufgabe zugrunde, diese Nachteile zu beheben und ein Einsatzelement bereitzustellen, mit dem es möglich ist, eine Laufschaufelreihe ohne Deckband in der Gasturbine zu betreiben.The present invention has for its object to overcome these disadvantages and to provide an insert element with which it is possible to operate a blade row without shroud in the gas turbine.

Gelöst wird diese Aufgabe mit einem Einsatzelement nach Anspruch 1 sowie einer Gasturbine nach Anspruch 5. 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 and a gas turbine according to claim 5. Advantageous developments of the invention are specified in the subclaims and described in the description.

Das erfindungsgemäße Einsatzelement zur Befestigung an einem Ringsegment einer Turbine einer Gasturbine weist eine konkav geformte Vorderseite und eine Rückseite mit zumindest einer Ausformung zur Positionierung an dem Ringsegment auf. Das Ringsegment ist dabei für einen Betrieb mit einer ein Deckband aufweisenden Laufschaufelreihe ausgebildet.The insert element according to the invention for fastening to a ring segment of a turbine of a gas turbine has a concave-shaped front side and a rear side with at least one shaping for positioning on the ring segment. The ring segment is designed for operation with a shroud having a shroud row.

Mit dieser Anordnung ist es vorteilhaft ermöglicht eine Gasturbine von einem Betrieb mit einer Laufschaufelreihe mit Deckband auf einen Betrieb mit einer Laufschaufelreihe ohne Deckband umzurüsten. Eine wesentlich aufwändigere Neuanfertigung eines passenden Ringsegments kann erspart bleiben.With this arrangement, it is advantageous to allow a gas turbine to convert from operation with a blade row with shroud to operation with a blade row without shroud. A much more complex new production of a suitable 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 Ringsegment befestigt werden.Thus, the insert element can be fastened with appropriate screws or bolts in a simple manner to the ring segment.

In einer weiteren vorteilhaften Ausgestaltung des erfindungsgemäßen Einsatzelements weist das Einsatzelement zumindest eine koaxial zum Kanal angeordnete Senkung an der Vorderseite auf.In a further advantageous embodiment of the insert element according to the invention, the insert element has at least one coaxial with the channel arranged reduction on the front side.

Die Befestigungsmittel, insbesondere der Kopf einer Schraube, kann dadurch in der Kontur des Einsatzelements versenkt werden.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 Ringsegment. Die Montage ist dadurch vereinfacht und mit weniger Aufwand möglich.The formations serve for easier, faster and more accurate positioning of the insert element before securing the insert element to the ring segment. The assembly is simplified and possible with less effort.

Das Einsatzelement ist bevorzugt in eine Gasturbine integriert. Die erfindungsgemäße Gasturbine umfasst eine Turbine mit einer Laufschaufelreihe und einem um die Laufschaufelreihe herum angeordneten Ringsegment. Das Ringsegment ist für einen Betrieb mit einer ein Deckband aufweisenden Laufschaufelreihe ausgebildet. Das Einsatzelement ist an dem Ringsegment befestigt.The insert element is preferably integrated in a gas turbine. The gas turbine according to the invention comprises a turbine with a blade row and a ring segment arranged around the blade row. The ring segment is for operation with a shroud row having a shroud educated. The insert element is attached to the ring segment.

Damit ist vorteilhaft eine Gasturbine bereitgestellt, die für einen Betrieb mit einer Laufschaufelreihe ohne Deckband geeignet 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 suitable for operation with a blade row without 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 therefore particularly suitable for experimental purposes in which frequent changes to the blades are made. 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 umgerüstet werden, indem das zumindest eine Einsatzelement vom Ringsegment entfernt wird.In addition, the gas turbine according to the invention can be converted 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.

Ausführungsbeispiele der Erfindung werden anhand der Zeichnungen und der nachfolgenden Beschreibung näher erläutert. Es zeigen:

Figur 1
eine erfindungsgemäße Gasturbine,
Figur 2
ein Detail der erfindungsgemäßen Gasturbine und
Figur 3
ein erfindungsgemäßes Einsatzelement.
Embodiments of the invention will be explained in more detail with reference to the drawings and the description below. Show it:
FIG. 1
a gas turbine according to the invention,
FIG. 2
a detail of the gas turbine according to the invention and
FIG. 3
an inventive insert element.

In der Figur 1 ist eine erfindungsgemäße Gasturbine 10 in einer beispielhaften Ausgestaltung skizziert. Die Gasturbine 10 umfasst erfindungsgemäß eine Turbine 11 in der wenigstens eine Laufschaufelreihe 12 angeordnet ist. Um diese Laufschaufelreihe 12 herum ist erfindungsgemäß ein Ringsegment 13 angeordnet. Die Laufschaufelreihe 12 ist um eine Rotationsachse 20 drehbar angeordnet.In the FIG. 1 a gas turbine 10 according to the invention is sketched in an exemplary embodiment. The gas turbine 10 according to the invention comprises a turbine 11 in which at least one blade row 12 is arranged. To this blade row 12 around a ring segment 13 is arranged according to the invention. 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 the FIG. 1 is the corresponding blade row 12, the fourth blade row of the turbine 11 of the gas turbine 10th

Die erfindungsgemäße Gasturbine 10 weist wenigstens ein an dem Ringsegment 13 befestigtes Einsatzelement 14 auf. In der Figur 2 ist die Anordnung des Einsatzelements 14 in dem Ringsegment in einer beispielhaften Ausgestaltung in einer Schnittdarstellung skizziert.The gas turbine 10 according to the invention has at least one insert element 14 fastened to the ring segment 13. In the FIG. 2 the arrangement of the insert member 14 in the ring segment is sketched in an exemplary embodiment in a sectional view.

Das Einsatzelement 14 deckt eine Aussparung 23 in dem Ringsegment 13 ab. Diese Aussparung 23 besitzt das Ringsegment 13 für den Betrieb der Gasturbine 10 mit einer Laufschaufelreihe, die ein Deckband aufweist. Um beispielsweise in einer Erprobungsphase nicht die gesamte obere Gehäusehälfte der Gasturbine abnehmen zu müssen (Cover-Lift) ist es vorteilhaft, die Laufschaufelreihe 12 ohne Deckband zu verwenden. Mittels des erfindungsgemäßen Einsatzelements 14 kann das Ringsegment 13 an die Laufschaufelreihe 12, die kein Deckband aufweist, angepasst werden.The insert element 14 covers a recess 23 in the ring segment 13. This recess 23 has the ring segment 13 for the operation of the gas turbine 10 with a blade row having a shroud. For example, in order not to have to remove the entire upper housing half of the gas turbine in a test phase (cover-lift), it is advantageous to use the blade row 12 without shroud. By means of the insert element 14 according to the invention, the ring segment 13 can be adapted to the blade row 12, which has no shroud.

Das in der Figur 3 in einer Einzelansicht gezeigte Einsatzelement 14 umfasst erfindungsgemäß eine konkav geformte Vorderseite 15 und eine Rückseite 16. An der Rückseite 16 weist das erfindungsgemäße Einsatzelement 14 zumindest eine Ausformung 17, 18 zur Positionierung an dem Ringsegment 13 auf.That in the FIG. 3 According to the invention, the insert element 14 shown in a single view comprises a concave front side 15 and a back side 16. At the rear side 16, the insert element 14 according to the invention has at least one projection 17, 18 for positioning on the ring segment 13.

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 M1 in einen Hinterschnitt 24 des Ringsegments 13 geschoben werden. Anschließend kann das Einsatzelement 14 in einem zweiten Montageschritt M2 an das Ringsegment 13 geklappt werden. Mit der oberen Ausformung 17 ist das Einsatzelement 14 dann in seiner Montageposition 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 Ringsegment 13 verschraubt werden. Die Mittel zum Verschrauben werden dabei durch die Kanäle 21 geführt. Das Einsatzelement 14 ist nach nur drei Montageschritten fest mit dem Ringsegment 13 verbunden. Das Einsatzelement 14 schließt in montiertem Zustand bevorzugt bündig mit dem Ringsegment 13 ab.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 13 in a first assembly step M1. Subsequently, the insert element 14 can be folded in a second assembly step M2 to the ring segment 13. With the upper molding 17, the insert member 14 is then positioned in its mounting position. The insert element 14 shown has two channels extending from the front side 15 to an upper side 22 21 on. In a third assembly step M3, the insert element 14 can now be screwed to the ring segment 13. The means for screwing are guided through the channels 21. The insert element 14 is firmly connected to the ring segment 13 after only three assembly steps. In the assembled state, the insert element 14 preferably ends flush with the ring segment 13.

Die Vorderseite 15 des erfindungsgemäßen Einsatzelements 14 ist konkav ausgeführt und damit dem um die Laufschaufelreihe 12 herum angeordneten Ringsegment 13 angepasst. Das gezeigte Einsatzelement 14 weist an der Vorderseite 15 jeweils eine Senkung 19 je Kanal 21 auf. Die Senkungen 19 sind jeweils koaxial zu den Kanälen 21 angeordnet.The front side 15 of the insert element 14 according to the invention is designed to be concave and thus adapted to the ring segment 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 depressions 19 are each arranged coaxially with the channels 21.

Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.Although the invention has been further illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.

Claims (5)

Einsatzelement (14) zur Befestigung an einem Ringsegment (13) einer Turbine (11) einer Gasturbine (10), welches für einen Betrieb mit einer ein Deckband aufweisenden Laufschaufelreihe ausgebildet ist,
wobei das Einsatzelement (14) eine konkav geformte Vorderseite (15) und eine Rückseite (16) mit zumindest einer Ausformung (17, 18) zur Positionierung an dem Ringsegment (13) aufweist.Insert element (14) for attachment to a ring segment (13) of a turbine (11) of a gas turbine (10), which is designed for operation with a shroud row having a shroud,
wherein the insert member (14) has a concave shaped front face (15) and a back face (16) with at least one formation (17, 18) for positioning on the ring segment (13). Einsatzelement (14) nach Anspruch 1,
wobei das Einsatzelement (14) zumindest einen von der Vorderseite (15) zu einer Oberseite (22) verlaufenden Kanal (21) aufweist.Insert element (14) according to claim 1,
wherein the insert element (14) has at least one channel (21) extending from the front side (15) to an upper side (22). Einsatzelement (14) nach Anspruch 1,
wobei das Einsatzelement (14) zumindest eine koaxial zum Kanal (21) angeordnete Senkung (19) an der Vorderseite (15) aufweist.Insert element (14) according to claim 1,
wherein the insert element (14) has at least one countersink (19) arranged coaxially with the channel (21) on the front side (15). Einsatzelement (14) nach einem der Ansprüche 1 bis 3,
wobei das Einsatzelement (14) eine obere Ausformung (17) und eine untere Ausformung (18) aufweist.Insert element (14) according to one of claims 1 to 3,
wherein the insert member (14) has an upper formation (17) and a lower formation (18). Gasturbine (10) mit einer eine Laufschaufelreihe (12) und ein um die Laufschaufelreihe (12) herum angeordnetes Ringsegment (13) aufweisenden Turbine (11),
wobei das Ringsegment (13) für einen Betrieb mit einer ein Deckband aufweisenden Laufschaufelreihe ausgebildet ist,
wobei die Gasturbine (10) zumindest ein an dem Ringsegment (13) befestigtes Einsatzelement (14) nach einem der Ansprüche 1 bis 4 aufweist.Gas turbine (10) having a turbine blade (11) having a blade row (12) and a ring segment (13) arranged around the blade row (12),
the ring segment (13) being designed for operation with a blade row having a cover band,
wherein the gas turbine (10) comprises at least one of the ring segment (13) fixed insert element (14) according to one of claims 1 to 4.
EP13185947.2A 2013-09-25 2013-09-25 Insert element and gas turbine Withdrawn EP2853685A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP13185947.2A EP2853685A1 (en) 2013-09-25 2013-09-25 Insert element and gas turbine
CN201480052860.8A CN105593470B (en) 2013-09-25 2014-08-29 Combustion gas turbine and installation method
US15/023,391 US10018051B2 (en) 2013-09-25 2014-08-29 Gas turbine and mounting method
JP2016516887A JP6227765B2 (en) 2013-09-25 2014-08-29 Gas turbine and mounting method
EP14758840.4A EP3022395B1 (en) 2013-09-25 2014-08-29 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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13185947.2A EP2853685A1 (en) 2013-09-25 2013-09-25 Insert element and gas turbine

Publications (1)

Publication Number Publication Date
EP2853685A1 true EP2853685A1 (en) 2015-04-01

Family

ID=49293459

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13185947.2A Withdrawn EP2853685A1 (en) 2013-09-25 2013-09-25 Insert element and gas turbine
EP14758840.4A Not-in-force EP3022395B1 (en) 2013-09-25 2014-08-29 Insert element and gas turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14758840.4A Not-in-force EP3022395B1 (en) 2013-09-25 2014-08-29 Insert element and gas turbine

Country Status (5)

Country Link
US (1) US10018051B2 (en)
EP (2) EP2853685A1 (en)
JP (1) JP6227765B2 (en)
CN (1) CN105593470B (en)
WO (1) WO2015043876A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11753938B2 (en) 2017-04-05 2023-09-12 Siemens Energy Global GmbH & Co. KG Method for sealing an annular gap in a turbine, and turbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0132182A1 (en) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine blade tip seal
GB2206651A (en) * 1987-07-01 1989-01-11 Rolls Royce Plc Turbine blade shroud structure
US20040120803A1 (en) * 2002-12-23 2004-06-24 Terrence Lucas Turbine shroud segment apparatus for reusing cooling air
EP2458152A2 (en) * 2010-11-29 2012-05-30 Alstom Technology Ltd Gas turbine of the axial flow type

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines
US3656862A (en) 1970-07-02 1972-04-18 Westinghouse Electric Corp Segmented seal assembly
JP2659950B2 (en) 1987-03-27 1997-09-30 株式会社東芝 Gas turbine shroud
US5165848A (en) * 1991-07-09 1992-11-24 General Electric Company Vane liner with axially positioned heat shields
US5195868A (en) * 1991-07-09 1993-03-23 General Electric Company Heat shield for a compressor/stator structure
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
JPH08277701A (en) * 1995-04-04 1996-10-22 Ishikawajima Harima Heavy Ind Co Ltd Structure for supporting stationary blade of turbine
DE19756734A1 (en) * 1997-12-19 1999-06-24 Bmw Rolls Royce Gmbh Passive gap system of a gas turbine
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
US6877952B2 (en) * 2002-09-09 2005-04-12 Florida Turbine Technologies, Inc Passive clearance control
DE102004016222A1 (en) * 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Arrangement for automatic running gap adjustment in a two-stage or multi-stage turbine
US7278820B2 (en) 2005-10-04 2007-10-09 Siemens Power Generation, Inc. Ring seal system with reduced cooling requirements
FR2922589B1 (en) * 2007-10-22 2009-12-04 Snecma CONTROL OF THE AUBES SET IN A HIGH-PRESSURE TURBINE TURBINE
FR2964145B1 (en) * 2010-08-26 2018-06-15 Safran Helicopter Engines TURBINE HOOD SHIELDING METHOD AND HITCH ASSEMBLY FOR ITS IMPLEMENTATION
EP2835504A1 (en) 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Insert element and gas turbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0132182A1 (en) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine blade tip seal
GB2206651A (en) * 1987-07-01 1989-01-11 Rolls Royce Plc Turbine blade shroud structure
US20040120803A1 (en) * 2002-12-23 2004-06-24 Terrence Lucas Turbine shroud segment apparatus for reusing cooling air
EP2458152A2 (en) * 2010-11-29 2012-05-30 Alstom Technology Ltd Gas turbine of the axial flow type

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11753938B2 (en) 2017-04-05 2023-09-12 Siemens Energy Global GmbH & Co. KG Method for sealing an annular gap in a turbine, and turbine
EP3574188B1 (en) * 2017-04-05 2024-02-28 Siemens Energy Global GmbH & Co. KG Method for sealing an annular gap in a turbine, and turbine

Also Published As

Publication number Publication date
CN105593470B (en) 2017-05-31
US10018051B2 (en) 2018-07-10
US20160201497A1 (en) 2016-07-14
CN105593470A (en) 2016-05-18
EP3022395A1 (en) 2016-05-25
WO2015043876A1 (en) 2015-04-02
JP6227765B2 (en) 2017-11-08
JP2016535188A (en) 2016-11-10
EP3022395B1 (en) 2017-08-16

Similar Documents

Publication Publication Date Title
DE954835C (en) Housing ring for centrifugal machines, especially for gas turbines
EP3152407B1 (en) Vane ring, inner ring, and turbomachine
DE102014114556A1 (en) Locking spacer assembly
CH702174A2 (en) Backup spacer assembly for an airfoil mounting system for introduction in the circumferential direction.
EP2873807A1 (en) Cover plate, rotor blade, wheel disc, bolt and gas turbine
DE102012100013A1 (en) Axial holding device for a turbine system
EP2505784B1 (en) Rotor for a turbomachine and corresponding upgrading method
EP2853685A1 (en) Insert element and gas turbine
EP3109520B1 (en) Seal carrier, guide blade assembly and fluid flow engine
DE102016203567A1 (en) Multi-vane stage turbomachine and method of partially dismantling such a turbomachine
EP2835500A1 (en) Insert element and gas turbine
DE102008051937A1 (en) Guide vane ring manufacturing method for steam turbine, involves removing processed guide vane ring from manufacturing device, and forming processed guide vane ring into guide vane support
EP2993305B1 (en) Gas turbine
EP3004562B1 (en) Insert element and gas turbine
DE102013220467A1 (en) Rotor having a rotor body and a plurality of blades mounted thereon
EP2824278B1 (en) Device, blade-device group, method and flow engine
CH705377A1 (en) A process for reconditioning a rotor of a turbomachine.
EP3015655A1 (en) Wheel disc assembly with seal plates
EP2886799A1 (en) Blade ring for a turbomachine and method for mounting blades of a blade ring of a turbomachine
EP2806108B1 (en) Connector and flow engine
DE102015224990A1 (en) Method for assembling a combustion chamber of a gas turbine engine
EP3025028B1 (en) Turbine blade and gas turbine
DE1476805A1 (en) Stator structure for flow machines
EP2818638B1 (en) Rotor-blade group, method and turbomachine
DE1269137B (en) Turbo machine runner

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20130925

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20151002