EP1462616A2 - Assembly for the axial and radial fastening of a guide vane ring in a casing of a turbomachine - Google Patents

Assembly for the axial and radial fastening of a guide vane ring in a casing of a turbomachine Download PDF

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Publication number
EP1462616A2
EP1462616A2 EP04002392A EP04002392A EP1462616A2 EP 1462616 A2 EP1462616 A2 EP 1462616A2 EP 04002392 A EP04002392 A EP 04002392A EP 04002392 A EP04002392 A EP 04002392A EP 1462616 A2 EP1462616 A2 EP 1462616A2
Authority
EP
European Patent Office
Prior art keywords
guide vane
housing
shaped
assembly
axial
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
EP04002392A
Other languages
German (de)
French (fr)
Other versions
EP1462616A3 (en
EP1462616B1 (en
Inventor
Alexander Böck
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.)
MTU Aero Engines AG
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MTU Aero Engines GmbH
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Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1462616A2 publication Critical patent/EP1462616A2/en
Publication of EP1462616A3 publication Critical patent/EP1462616A3/en
Application granted granted Critical
Publication of EP1462616B1 publication Critical patent/EP1462616B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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

Definitions

  • the invention relates to an arrangement for the axial and radial fixing of a guide vane assembly in the housing of a turbine engine with a locking ring, which in a corresponding radial groove engages in the facing wall of the housing and is secured against radial evasion by means of a locking element.
  • vane clusters It is known as vane clusters called vane assemblies as a unit from behind to be inserted into the housing of a turbine engine and inserted into the Position by means of piston rings similar to circlips, which are provided for this purpose Corresponding grooves are inserted in the inserted position.
  • the retaining rings themselves are replaced by a subsequent component, usually by an as Liner designated turbine belt segment locked, which the radial sliding out of the Circlip prevented from the assigned groove.
  • the subsequent turbine shroud segment must be designed such that it can overlap the guide vane assembly by means of a hook-shaped rear edge.
  • This object is achieved according to the invention using a locking ring in that that the locking ring is approximately L-shaped in cross section, the longer one Leg engages in the radial groove of the wall of the housing and its short leg a hook-shaped projection on the respective blade head of the guide blades of the guide blade group engages behind, as well as by means of a subsequent turbine shroud segment attached clamp held on the short leg held in its secure position is.
  • the inventive solution does not require any axial webs to accommodate the otherwise common locking pins still a large length to accommodate the thermal axial Tolerances and thus avoids relatively high axial space requirements.
  • the invention is based on a more or less schematic in the drawing illustrated embodiment described.
  • FIG. 1 From an axially and radially immovable held in the housing of a turbine engine Guide vane assembly in FIG. 1 is only a guide vane 10 with its head part 11 and the associated inner region of the housing 14 of such an arrangement according to the State of the art shown. With this arrangement, the vane assembly is fixed via a locking ring 15. For this purpose, there is a groove 18 in the housing 14 for receiving the locking ring 15 is provided, on which a flange-like extension 19 of the Bucket head 11 abuts. The extension has an opening 20 into which a corresponding one flange-like extension 21 of the housing 14 secured securing pin 23 in order to prevent the guide vane assembly from slipping radially out with bearing play intervenes.
  • the locking ring is locked radially by means of a Inner circumferential surface of the locking ring cam 25, which on the facing Front side of the downstream downstream assembly 26 of the Turbine engine is attached.
  • the upstream end of the blade head 11 engages with an extension 27 into an associated recess 28 of the housing 14.
  • a locking ring is also provided there, which is designated by the reference number 30 is and in contrast to the known circlips an L-shaped cross section having.
  • the securing ring 30 engages with its long leg 32 in the housing 14 provided groove 18 a.
  • the short leg 33 encompasses a suitably trained one short hook-shaped extension 34 on the blade head 11 of the associated guide blade 10 of the guide vane assembly to be held and forms with its end face 35 Contact surface for the circlip 30.
  • a U-shaped bracket 36 is provided, which at the front end 24 of the following Assembly 26 of the turbine engine is attached and with its free leg 38 engaging under the short leg 33 of the retaining ring 30.
  • the U-shaped Bracket 36 is, as described in connection with FIG. 2, with the facing End 24 of the following downstream bow section 26, which is referred to as liner, is firmly connected and engages in the recess 29 in the housing 14.
  • the locking ring 30 and thus the guide vane assembly are radial and axially in their predetermined position in the housing 14 of the turbine engine, not shown kept immovable.

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

Abstract

The arrangement for the axial and radial fixing of a guide vane assembly in the casing of a gas turbine engine has a piston ring type locking ring (30) which in cross section is L-shaped, with the long side (32) engaging in a radial slot (18) in the wall of the casing (14), and the short side (33) fitting behind a hook-form protrusion (34) on each blade head (11). The locking ring is held in its locked position by means of a U-shaped clamp (36) which is fastened on the subsequent turbine shroud segment (26) and which lies against the short side.

Description

Die Erfindung betrifft eine Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes mit einem Sicherungsring, der in eine korrespondierende radiale Nut in der zugewandten Wandung des Gehäuses eingreift und mittels eines Verriegelungselementes gegen radiales Ausweichen gesichert ist.The invention relates to an arrangement for the axial and radial fixing of a guide vane assembly in the housing of a turbine engine with a locking ring, which in a corresponding radial groove engages in the facing wall of the housing and is secured against radial evasion by means of a locking element.

Es ist bekannt als Vane-Kluster bezeichnete Leitschaufelbaugruppen als Baueinheit von hinten in das Gehäuse eines Turbinentriebwerkes einzuschieben und in der eingeschobenen Lage mittels Kolbenringen ähnlichen Sicherungsringen, die in hierfür vorgesehene mit diesen korrespondierenden Nuten eingelegt werden, in der eingeschobenen Lage festzulegen. Die Sicherungsringe selbst werden durch ein nachfolgendes Bauteil, meist durch ein als Liner bezeichnetes Turbinenbandsegment verriegelt, welches das radiale Herausgleiten des Sicherungsringes aus der zugeordneten Nut verhindert. Für eine solche Sicherung durch das nachfolgende Turbinendeckbandsegment muss dieses derart ausgebildet sein, dass es mittels einer hakenförmigen Hinterkante die Leitschaufelbaugruppe übergreifen kann.It is known as vane clusters called vane assemblies as a unit from behind to be inserted into the housing of a turbine engine and inserted into the Position by means of piston rings similar to circlips, which are provided for this purpose Corresponding grooves are inserted in the inserted position. The retaining rings themselves are replaced by a subsequent component, usually by an as Liner designated turbine belt segment locked, which the radial sliding out of the Circlip prevented from the assigned groove. For such a backup the subsequent turbine shroud segment must be designed such that it can overlap the guide vane assembly by means of a hook-shaped rear edge.

Es ist auch bekannt, die Zuordnung der Bauteile einer solchen Anordnung durch axiale Stifte am Gehäuse, die in korrespondierende Bohrungen in der Leitschaufelbaugruppe eingreifen, zu sichern.It is also known to assign the components of such an arrangement by means of axial pins on the housing, which engage in corresponding bores in the guide vane assembly, to secure.

Das bekannte relativ einfach herzustellende Festlegen der Leitschaufelbaugruppe im Gehäuse des Turbinentriebwerkes mittels Sicherungsringen oder mittels Liner hat jedoch Nachteile. Entweder werden radiale Stege am Gehäuse zur Aufnahme der axialen Stifte benötigt, was großen Bauaufwand, höheres Gewicht und größere Kosten bedeutet. Eine Sicherung durch die nachfolgende Baugruppe baut demgegenüber relativ lang, da das während des Betriebes infolge der thermischen Wanderung des den Sicherungsring in seiner Lage zu haltende Turbinendeckbandsegment lang genug ausgebildet werden muss, um die dabei auftretenden axialen Toleranzen ausgleichen zu können. The known, relatively easy to manufacture, fixing of the guide vane assembly in the housing the turbine engine by means of circlips or liner Disadvantage. Either radial bars on the housing are required to accommodate the axial pins, which means great construction costs, higher weight and higher costs. A backup by the following assembly, on the other hand, builds relatively long, because that during of the operation due to the thermal migration of the circlip in position Holding turbine shroud segment must be formed long enough to do this to be able to compensate for any axial tolerances.

Hier Abhilfe zu schaffen, ist Aufgabe der Erfindung.To remedy this is the object of the invention.

Diese Aufgabe ist unter Verwendung eines Sicherungsringes erfindungsgemäß dadurch gelöst, dass der Sicherungsring im Querschnitt etwa L-förmig ausgebildet ist, dessen langer Schenkel in die radiale Nut der Wandung des Gehäuses eingreift und dessen kurzer Schenkel einen hakenförmigen Vorsprung am jeweiligen Schaufelkopf der Leitschaufeln der Leitschaufelgruppe hintergreift, sowie mittels einer am nachfolgenden Turbinendeckbandsegment befestigten am kurzen Schenkel anliegenden Klammer in seiner Sicherungslage gehalten ist.This object is achieved according to the invention using a locking ring in that that the locking ring is approximately L-shaped in cross section, the longer one Leg engages in the radial groove of the wall of the housing and its short leg a hook-shaped projection on the respective blade head of the guide blades of the guide blade group engages behind, as well as by means of a subsequent turbine shroud segment attached clamp held on the short leg held in its secure position is.

Die erfinderische Lösung benötigt weder axiale Stege zur Aufnahme der sonst üblichen Sicherungsstifte noch eine große Baulänge zur Aufnahme der thermisch bedingten axialen Toleranzen und vermeidet damit relativ hohen axialen Platzbedarf. Darüber hinaus wird infolge Wegfall der Sicherungsstifte und deren Mittel zur Lagerung an Gewicht und Arbeitsaufwand gespart.The inventive solution does not require any axial webs to accommodate the otherwise common locking pins still a large length to accommodate the thermal axial Tolerances and thus avoids relatively high axial space requirements. In addition, as a result Elimination of the locking pins and their means of storage in terms of weight and labor saved.

Die Erfindung ist nachfolgend anhand eines in der Zeichnung mehr oder minder schematisch dargestellten Ausführungsbeispiels beschrieben.The invention is based on a more or less schematic in the drawing illustrated embodiment described.

Es zeigen:

Fig. 1
das Konzept einer Anordnung zur Sicherung einer Leitschaufelbaugruppe eines Turbinentriebwerkes in dem diese lagernden Gehäuse mit Hilfe eines mittels Stifte festgelegten Sicherungsringes, teilweise im Schnitt dargestellt, nach dem Stande der Technik,
Fig. 2
eine abgewandelte Ausführungsform einer Anordnung nach dem Stande der Technik, bei der das Festlegen des Sicherungsringes mittels einer am nachfolgenden Turbinendeckband befindlichen Klammer erfolgt und
Fig. 3
die Ausbildung einer Anordnung zur Sicherung einer Leitschaufelbaugruppe eines Turbinentriebwerkes in dem diese lagernden Gehäuse gemäß der Erfindung.
Show it:
Fig. 1
the concept of an arrangement for securing a guide vane assembly of a turbine engine in the housing supporting it with the aid of a retaining ring fixed by means of pins, partially shown in section, according to the prior art,
Fig. 2
a modified embodiment of an arrangement according to the prior art, in which the securing ring is fixed by means of a clamp located on the subsequent turbine shroud and
Fig. 3
the formation of an arrangement for securing a guide vane assembly of a turbine engine in the housing supporting this according to the invention.

Von einer im Gehäuse eines Turbinentriebwerkes axial und radial unverrückbar gehaltenen Leitschaufelbaugruppe ist in Fig. 1 lediglich eine Leitschaufel 10 mit ihrem Kopfteil 11 und der dazugehörige innere Bereich des Gehäuses 14 einer solchen Anordnung nach dem Stande der Technik gezeigt. Bei dieser Anordnung erfolgt das Festlegen der Leitschaufelbaugruppe über ein Sicherungsring 15. Hierzu ist im Gehäuse 14 eine Nut 18 für die Aufnahme des Sicherungsringes 15 vorgesehen, an dem ein flanschartiger Fortsatz 19 des Schaufelkopfes 11 anliegt. Der Fortsatz weist eine Öffnung 20 auf, in die ein in einem korrespondierenden flanschartigen Fortsatz 21 des Gehäuses 14 befestigter Sicherungsstift 23 zwecks Verhinderung des radialen Herausrutschens der Leitschaufelbaugruppe mit Lagerspiel eingreift. Die radiale Verriegelung des Sicherungsringes erfolgt mittels eines an der Innenmantelfläche des Sicherungsringes anliegenden Nockens 25, der an der zugewandten Stirnseite der als "Liner" bezeichneten nachfolgenden stromabliegenden Baugruppe 26 des Turbinentriebwerkes befestigt ist. Das stromaufliegende Ende des Schaufelkopfes 11 greift mit einem Fortsatz 27 in eine diesem zugeordnete Ausnehmung 28 des Gehäuses 14 ein.From an axially and radially immovable held in the housing of a turbine engine Guide vane assembly in FIG. 1 is only a guide vane 10 with its head part 11 and the associated inner region of the housing 14 of such an arrangement according to the State of the art shown. With this arrangement, the vane assembly is fixed via a locking ring 15. For this purpose, there is a groove 18 in the housing 14 for receiving the locking ring 15 is provided, on which a flange-like extension 19 of the Bucket head 11 abuts. The extension has an opening 20 into which a corresponding one flange-like extension 21 of the housing 14 secured securing pin 23 in order to prevent the guide vane assembly from slipping radially out with bearing play intervenes. The locking ring is locked radially by means of a Inner circumferential surface of the locking ring cam 25, which on the facing Front side of the downstream downstream assembly 26 of the Turbine engine is attached. The upstream end of the blade head 11 engages with an extension 27 into an associated recess 28 of the housing 14.

Bei der Anordnung nach Fig. 2 tragen einander entsprechende bzw. gleiche Bauteile gleiche Bezugsziffern. An Stelle eines Sicherungsstiftes ist dort eine den Sicherungsring 15 untergreifende U-förmige Klammer 23 vorgesehen, die an dem zugewandten Ende 24 der nachfolgenden stromabliegenden Baugruppe 26 des Turbinentriebwerkes, also dem "Liner", starr befestigt ist und mit diesem in einer Ausnehmung 29 des Gehäuses 14 eingreift. Der freie Schenkel 16 der U-förmigen Klammer 23 untergreift einen hakenförmigen Fortsatz 17 am Kopfteil 11 der Leitschaufel 10.In the arrangement according to FIG. 2, corresponding or identical components have the same components Reference numerals. Instead of a locking pin there is a retaining ring 15 that engages under it U-shaped bracket 23 provided on the facing end 24 of the following downstream assembly 26 of the turbine engine, ie the "liner", rigid is attached and engages with this in a recess 29 of the housing 14. The free one Leg 16 of the U-shaped bracket 23 engages under a hook-shaped extension 17 on Head part 11 of the guide vane 10.

Diese verhältnismäßig aufwendigen Konstruktionen nach den Fig. 1 und 2 ersetzt die Ausbildung nach Fig. 3.These relatively complex constructions according to FIGS. 1 and 2 replace the training 3.

Auch dort tragen die in den Fig. 1 und 2 entsprechenden Bauteile die gleichen Bezugsziffern. Auch dort ist ein Sicherungsring vorgesehen, der mit der Bezugsziffer 30 bezeichnet ist und im Gegensatz zu den bekannten Sicherungsringen einen L-förmigen Querschnitt aufweist. Der Sicherungsring 30 greift mit seinem langen Schenkel 32 in die im Gehäuse 14 vorgesehenen Nut 18 ein. Der kurze Schenkel 33 umgreift einen entsprechend ausgebildeten kurzen hakenförmigen Fortsatz 34 am Schaufelkopf 11 der jeweils zugeordneten Leitschaufel 10 der zu haltenden Leitschaufelbaugruppe und bildet mit seiner Stirnseite 35 die Anlagefläche für den Sicherungsring 30.There, too, the components corresponding to FIGS. 1 and 2 have the same reference numbers. A locking ring is also provided there, which is designated by the reference number 30 is and in contrast to the known circlips an L-shaped cross section having. The securing ring 30 engages with its long leg 32 in the housing 14 provided groove 18 a. The short leg 33 encompasses a suitably trained one short hook-shaped extension 34 on the blade head 11 of the associated guide blade 10 of the guide vane assembly to be held and forms with its end face 35 Contact surface for the circlip 30.

Ferner ist eine U-förmige Klammer 36 vorgesehen, die am stirnseitigen Ende 24 der nachfolgenden Baugruppe 26 des Turbinentriebwerkes befestigt ist und mit ihrem freien Schenkel 38 am kurzen Schenkel 33 des Sicherungsringes 30 anliegend diesen untergreift. Die U-förmige Klammer 36 ist, wie in Verbindung mit Fig. 2 beschrieben, mit dem zugewandten Ende 24 der nachfolgenden stromabliegenden als Liner bezeichneten Bugruppe 26 fest verbunden und greift in die Ausnehmung 29 im Gehäuse 14 ein.Furthermore, a U-shaped bracket 36 is provided, which at the front end 24 of the following Assembly 26 of the turbine engine is attached and with its free leg 38 engaging under the short leg 33 of the retaining ring 30. The U-shaped Bracket 36 is, as described in connection with FIG. 2, with the facing End 24 of the following downstream bow section 26, which is referred to as liner, is firmly connected and engages in the recess 29 in the housing 14.

Auf diese Weise sind der Sicherungsring 30 und damit die Leitschaufelbaugruppe radial und axial in ihrer vorbestimmten Lage im Gehäuse 14 des nicht näher dargestellten Turbinentriebwerkes unverrückbar gehalten. In this way, the locking ring 30 and thus the guide vane assembly are radial and axially in their predetermined position in the housing 14 of the turbine engine, not shown kept immovable.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

1010
Leitschaufelvane
1111
Schaufelkopfshovel head
1414
Gehäusecasing
1515
Sicherungsringcirclip
1616
Schenkelleg
1717
Fortsatzextension
1818
Nut im GehäuseGroove in the housing
1919
Fortsatzextension
2020
Öffnungopening
2121
Fortsatzextension
2323
Sicherungsstift, U-förmige KlammerLocking pin, U-shaped bracket
2424
Ende der nachfolgenden BaugruppeEnd of the subsequent assembly
2525
Nockencam
2626
TurbinenbandsegmentTurbine band segment
2727
Fortsatzextension
2828
Ausnehmung im GehäuseRecess in the housing
2929
Ausnehmung im GehäuseRecess in the housing
3030
Sicherungsringcirclip
3232
langer Schenkellong leg
3333
kurzer Schenkelshort leg
3434
hakenförmiger Vorsprunghook-shaped projection
3535
Stirnseite des VorsprungesFront of the projection
3636
U-förmige KlammerU-shaped bracket
3838
freier Schenkel der Klammer 36free leg of the clamp 36
3939
zweiter Schenkel der Klammer 36second leg of the clamp 36

Claims (3)

Anordnung für das axiale und radiale Festlegen einer Leitschaufelgruppe in dem Gehäuse eines Turbinentriebwerkes mit einem kolbenringförmigen Sicherungsring, der in eine korrespondierende radiale Nut in der zugewandten Wandung des Gehäuses eingreift und mittels eines Verriegelungselementes gegen radiales Ausweichen gesichert ist, dadurch gekennzeichnet, dass der Sicherungsring (30) im Querschnitt etwa L-förmig ausgebildet ist, dessen langer Schenkel (32) in die radiale Nut (18) der Wandung des Gehäuses (14) eingreift und dessen kurzer Schenkel (33) einen hakenförmigen Vorsprung (34) am Schaufelkopf (11) jeder Leitschaufel der Leitschaufelbaugruppe hintergreift sowie mittels einer am nachfolgenden Turbinenbandsegment (26) befestigten am kurzen Schenkel (33) anliegenden U-förmigen Klammer (36) in seiner Sicherungslage gehalten ist.Arrangement for the axial and radial fixing of a guide vane group in the housing of a turbine engine with a piston ring-shaped locking ring which engages in a corresponding radial groove in the facing wall of the housing and is secured against radial evasion by means of a locking element, characterized in that the locking ring (30 ) is approximately L-shaped in cross section, whose long leg (32) engages in the radial groove (18) of the wall of the housing (14) and whose short leg (33) has a hook-shaped projection (34) on the blade head (11) each The guide vane engages behind the guide vane assembly and is held in its securing position by means of a U-shaped bracket (36) attached to the short leg (33) and attached to the subsequent turbine belt segment (26). Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Stirnseite des hakenförmigen Vorsprunges (34) die die axiale Lage der Leitschaufelbaugruppe bestimmende Anschlagfläche (35) für den Sicherungsring (30) bildet.Arrangement according to claim 1, characterized in that the end face of the hook-shaped projection (34) forms the stop surface (35) for the locking ring (30) which determines the axial position of the guide vane assembly. Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass der mit dem stirnseitigen Ende der nachfolgenden Baugruppe (Liner 26) verbundene Schenkel (39) der U-förmigen Klammer (36) in eine Ausnehmung (29) des Gehäuses (14) des Turbinentriebwerkes eingreift.Arrangement according to claim 1, characterized in that the leg (39) of the U-shaped bracket (36) connected to the front end of the subsequent assembly (liner 26) engages in a recess (29) in the housing (14) of the turbine engine.
EP20040002392 2003-03-22 2004-02-04 Assembly for the axial and radial fastening of a guide vane ring in a casing of a turbine engine Expired - Lifetime EP1462616B1 (en)

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Application Number Priority Date Filing Date Title
DE2003112956 DE10312956B4 (en) 2003-03-22 2003-03-22 Arrangement for the axial and radial fixing of a guide vane assembly in the housing of a turbine engine
DE10312956 2003-03-22

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EP1462616A2 true EP1462616A2 (en) 2004-09-29
EP1462616A3 EP1462616A3 (en) 2009-09-30
EP1462616B1 EP1462616B1 (en) 2011-06-15

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CN101460709B (en) * 2006-04-06 2011-11-02 西门子公司 Stator vane segment for a turbomachine, associated manufacturing method and turbomachine
FR2960591A1 (en) * 2010-06-01 2011-12-02 Snecma DEVICE FOR ROTATING A DISPENSING SEGMENT IN A TURBOMACHINE HOUSING; PION ANTIROTATION
FR2985792A1 (en) * 2012-01-18 2013-07-19 Snecma ANGLE CORRELATION VIBRATION DAMPING RECTIFIER SECTOR FOR TURBOMACHINE COMPRESSOR
WO2013156734A1 (en) * 2012-04-20 2013-10-24 Snecma Turbine stage for a turbomachine
EP2787178A1 (en) 2013-04-03 2014-10-08 MTU Aero Engines GmbH Guide vane assembly
DE102016203567A1 (en) * 2016-03-04 2017-09-07 Siemens Aktiengesellschaft Multi-vane stage turbomachine and method of partially dismantling such a turbomachine
EP3000990B1 (en) 2014-09-26 2019-05-29 Rolls-Royce plc A shroud segment retainer of a turbine
FR3083820A1 (en) * 2018-07-11 2020-01-17 Safran Aircraft Engines IMPROVED HOLDING DEVICE FOR A TURBOMACHINE DISPENSER

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DE102014209057A1 (en) 2014-05-14 2015-11-19 MTU Aero Engines AG Gas turbine casing assembly
DE102020201448A1 (en) 2020-02-06 2021-08-12 Siemens Aktiengesellschaft Additively manufactured turbine blade with anti-twist device and adjustment process
CN112177689A (en) * 2020-09-29 2021-01-05 中国航发湖南动力机械研究所 Turbine guider positioning structure of engine and engine

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CN101460709B (en) * 2006-04-06 2011-11-02 西门子公司 Stator vane segment for a turbomachine, associated manufacturing method and turbomachine
US8128357B2 (en) 2006-04-06 2012-03-06 Siemens Aktiengesellschaft Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine
FR2923526A1 (en) * 2007-11-13 2009-05-15 Snecma Sa TURBINE OR TURBOMACHINE COMPRESSOR STAGE
EP2060744A1 (en) * 2007-11-13 2009-05-20 Snecma Stage of a turbine or turbomachine compressor
US8277179B2 (en) 2007-11-13 2012-10-02 Snecma Turbine or compressor stage for a turbomachine
FR2960591A1 (en) * 2010-06-01 2011-12-02 Snecma DEVICE FOR ROTATING A DISPENSING SEGMENT IN A TURBOMACHINE HOUSING; PION ANTIROTATION
WO2011151596A1 (en) * 2010-06-01 2011-12-08 Snecma Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg
CN102918230A (en) * 2010-06-01 2013-02-06 斯奈克玛 Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing
US20130078086A1 (en) * 2010-06-01 2013-03-28 Snecma Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg
US9562441B2 (en) 2010-06-01 2017-02-07 Snecma Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg
CN102918230B (en) * 2010-06-01 2015-08-26 斯奈克玛 With the turbo machine of the device for preventing the sector of nozzle guide vanes assembly from rotating in housing; Anti-rotational bolt
RU2558174C2 (en) * 2010-06-01 2015-07-27 Снекма Gas turbine engine with device for locking of distributor revolution in case and revolution locking pin
GB2513754A (en) * 2012-01-18 2014-11-05 Snecma Angular downstream guide vane sector with vibration damping by means of a wedge for a turbine engine compressor
WO2013107967A1 (en) * 2012-01-18 2013-07-25 Snecma Angular downstream guide vane sector with vibration damping by means of a wedge for a turbine engine compressor
GB2513754B (en) * 2012-01-18 2017-11-22 Snecma An angular diffuser sector for a turbine engine compressor, with a vibration damper wedge
US9709072B2 (en) 2012-01-18 2017-07-18 Snecma Angular diffuser sector for a turbine engine compressor, with a vibration damper wedge
FR2985792A1 (en) * 2012-01-18 2013-07-19 Snecma ANGLE CORRELATION VIBRATION DAMPING RECTIFIER SECTOR FOR TURBOMACHINE COMPRESSOR
WO2013156734A1 (en) * 2012-04-20 2013-10-24 Snecma Turbine stage for a turbomachine
CN104246141B (en) * 2012-04-20 2016-08-24 斯奈克玛 For the stage of turbine of turbine engine and include the turbine engine of this stage of turbine
JP2015514907A (en) * 2012-04-20 2015-05-21 スネクマ Turbine stage for turbine engine
CN104246141A (en) * 2012-04-20 2014-12-24 斯奈克玛 Turbine stage for a turbomachine
RU2633316C2 (en) * 2012-04-20 2017-10-11 Снекма Turbine stage of turbine engine and turbomachine
FR2989724A1 (en) * 2012-04-20 2013-10-25 Snecma TURBINE STAGE FOR A TURBOMACHINE
US9957841B2 (en) 2012-04-20 2018-05-01 Snecma Turbine stage for a turbine engine
EP2787178A1 (en) 2013-04-03 2014-10-08 MTU Aero Engines GmbH Guide vane assembly
EP3000990B1 (en) 2014-09-26 2019-05-29 Rolls-Royce plc A shroud segment retainer of a turbine
DE102016203567A1 (en) * 2016-03-04 2017-09-07 Siemens Aktiengesellschaft Multi-vane stage turbomachine and method of partially dismantling such a turbomachine
US10844747B2 (en) 2016-03-04 2020-11-24 Siemens Aktiengesellschaft Continuous flow machine having multiple guide vane stages and method for partially disassembling a continuous flow machine of this type
FR3083820A1 (en) * 2018-07-11 2020-01-17 Safran Aircraft Engines IMPROVED HOLDING DEVICE FOR A TURBOMACHINE DISPENSER

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DE10312956B4 (en) 2011-08-11
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DE10312956A1 (en) 2004-09-30

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