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EP1694943B1 - Turbomachine - Google Patents

Turbomachine Download PDF

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Publication number
EP1694943B1
EP1694943B1 EP04802843.5A EP04802843A EP1694943B1 EP 1694943 B1 EP1694943 B1 EP 1694943B1 EP 04802843 A EP04802843 A EP 04802843A EP 1694943 B1 EP1694943 B1 EP 1694943B1
Authority
EP
European Patent Office
Prior art keywords
guide
housing
fork
shaped elements
turbomachine
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.)
Expired - Lifetime
Application number
EP04802843.5A
Other languages
German (de)
French (fr)
Other versions
EP1694943A2 (en
Inventor
Gerhard BRÜCKNER
Manfred Feldmann
Bernd Kislinger
Joachim Wulf
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
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines 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 MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP1694943A2 publication Critical patent/EP1694943A2/en
Application granted granted Critical
Publication of EP1694943B1 publication Critical patent/EP1694943B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of patent claim 1.
  • Turbomachines for example gas turbines, have a rotor and a stator, the rotor having a housing and vanes together with the same rotating blades and the stator.
  • the blades associated with the rotor rotate with respect to the fixed housing and fixed stator vanes.
  • the vanes form vane rings and the blades form rotor blade rings, wherein in each case a rotor blade ring is positioned between two guide vane rings arranged one behind the other in the flow direction.
  • the Leitschaufelkränze border with a radially outer end, in particular with an outer shroud, to the housing and with a radially inner end, in particular with an inner shroud, to the rotor.
  • the vane rings are attached to the housing of the turbomachine and may be memory centered with respect to the housing.
  • the document DE 198 07 247 A1 discloses such a turbomachine, wherein for the centering and fixing of the guide vane rings bearing journals are provided.
  • the housing-fixed journals penetrate the housing of the turbomachine and engage for the centering of the center of the vane rings in the guide vane rings associated bearing bushes.
  • the guide pins penetrate the housing of the turbomachine in the radial direction, a longitudinal center axis of the bearing bushes thus runs parallel to the radial direction of the turbomachine, wherein the corresponding bearing bushes are also aligned in the radial direction of the turbomachine.
  • seal carrier are positioned between two adjacent Leitschaufelkränzen, wherein the seal carrier are mounted in the outer shrouds of the Leitschaufelkränze.
  • the document US-A-2,801,075 protects a turbomachine with stator and rotor, in which at least one vane ring is memory-centered relative to the housing, while the housing extending from the outside penetrating bearing pins or guide pins approximately perpendicular to the housing wall.
  • the document U.S. Patent 5,775,874 relates to a turbomachine with stator and rotor, wherein at least one vane ring is composed of a plurality of vane segments. Each vane segment is stretched radially outwardly against the housing via a U-shaped bracket. In addition, the housing from the outside about perpendicularly penetrating pins are present, which secure the vane segments against rotation in the circumferential direction.
  • the document US-A-3 104 091 discloses a turbomachine with stator and rotor in which at least one vane ring is memory-centered with respect to the housing.
  • the bearing pins or guide pins are arranged axially within the housing.
  • the present invention is based on the problem of providing a novel turbomachine.
  • the guide pins extend approximately perpendicular to the housing, wherein projecting into the housing ends of the guide pins in the radially outer ends of the guide vane rings associated, fork-shaped elements engage.
  • both the guide vane rings and the seal carrier are memory-centered by means of the guide pins and the fork-shaped elements.
  • Each fork-shaped element preferably defines at least two recesses or receiving spaces, wherein the guide pins engage in a first recess and wherein projections of the seal carrier engage in a second recess.
  • the two recesses of the fork-shaped elements are positioned next to each other in the circumferential direction.
  • the guide pins In a tapered or widening housing, z. B. conical housing wall, the guide pins therefore do not extend in the radial direction of the turbomachine, but on the one hand obliquely to the radial direction and on the other hand obliquely to the axial direction of the turbomachine.
  • the guide pins In the housing projecting ends of the guide pins thus also extend obliquely to the axial direction and radial direction of the turbomachine and cooperate with fork-shaped elements in the vane rings, the fork-shaped elements in the radial direction and axial direction of the turbomachine are at least partially open, to intervene in the Casing projecting ends of the guide pins in the fork-shaped elements to allow.
  • the present invention is generally suitable for all turbomachinery with rotor and stator.
  • the invention is suitable for use in a compressor or a turbine of a gas turbine, in particular an aircraft engine.
  • Fig. 1 a partial, axial longitudinal section through a low-pressure turbine shows.
  • Fig. 1 shows a section of a low-pressure turbine 10 in the range of two vane rings 11 and 12 and two blade rings 13 and 14. Die Leit Blade rings 11 and 12 and blade rings 13 and 14 are alternately positioned one behind the other in the axial direction of the low-pressure turbine 10.
  • the axial direction of the low-pressure turbine 10 is in Fig. 1 represented by an arrow 15, the radial direction thereof by an arrow 16th
  • Each of the vane rings 11 and 12 is formed by a plurality of circumferentially of the low-pressure turbine 10 juxtaposed vanes 17, wherein Fig. 1 only the radially outer ends 18 of the vanes 17 shows. In the region of the radially outer ends 18 of the guide vanes 17 so-called outer shrouds 19 are formed.
  • the vane rings 11 and 12 are associated with a stator of the low-pressure turbine 10, wherein the stator in addition to the vanes 17 of the vane rings 11 and 12 and a housing 20 includes.
  • the housing 20 and the vane rings 11 and 12 are fixed, wherein the rotor blades associated with a rotor blades 13 and 14 with respect to the fixed vane rings 11 and 12 and the fixed housing 20 rotate.
  • Each of the rotating blade rings 13 and 14 is thereby formed by a plurality of circumferentially of the low-pressure turbine 10 juxtaposed blades 21, wherein Fig. 1 again only the radially outer ends 22 of the blades 21 shows.
  • outer shrouds 23 are formed in turn.
  • the centering and fixing of the vane rings 11 and 12 via bearing pins or guide pins 24 takes place, wherein the guide pins 24 extend approximately perpendicular to the housing 20.
  • Fig. 1 can be removed, is a longitudinal central axis 25 of the guide pins 24 approximately perpendicular to the housing 20 and thus extends obliquely to the radial direction (arrow 16) and axial direction (arrow 15) of the low-pressure turbine 10.
  • ends 26 protrude the guide pins 24 into the housing 20 and thereby engage for centering and fixing the guide vane rings 11 and 12 in fork-shaped elements 27, which are the outer shrouds 19 of the vane rings 11 and 12 associated.
  • a plurality of fork-shaped elements 27 are positioned over the circumference of the outer shrouds of the guide vane rings 11 and 12, wherein in each of the fork-shaped elements 27 of a guide vane ring 11 and 12, a corresponding guide pin 24 engages, wherein the guide pins 24 are arranged distributed according to the fork-shaped elements 27 over the circumference of the housing.
  • guide pins 24 are arranged distributed according to the fork-shaped elements 27 over the circumference of the housing.
  • guide pins 24 are required, which cooperate with corresponding fork-shaped elements 27 in the region of the outer shrouds 19 of the guide vane rings 11 and 12.
  • per guide vane ring 11 and 12 seven such pairs of guide pins 24 and fork-shaped elements 27 are arranged distributed over the circumference of the low-pressure turbine 10.
  • the fork-shaped elements 27 in the region of the outer shrouds 19 of the Leitschaufelkränze 11 and 12 are at least partially open in the radial direction and in the axial direction of the low-pressure turbine 10 to allow engagement of the projecting into the housing 20 ends 26 of the guide pins 24 in the fork-shaped elements 27.
  • the fork-shaped elements 27 of the vane rings 11 and 12 together with the guide pins 24 not only fixation and centering of the vane rings 11 and 12 on the housing, but also a fixation and centering of seal carriers 28, between adjacent outer shrouds 18 adjacent vane rings 11 and 12 are arranged.
  • the seal carrier 28 carry in the embodiment shown as a honeycomb seals sealing body 29, which cooperate with so-called sealing fins 30 in the outer shrouds 23 of the blade rings 13 and 14 and a seal of a gap between the radially outer ends 22 of the blades 21 and the housing 20 of the low-pressure turbine 10th cause.
  • the fork-shaped element 27 has two recesses 31 and 32.
  • the two recesses 31 and 32 are partially open both in the radial direction and in the axial direction of the low-pressure turbine 10 and in the circumferential direction of the same side by side.
  • a first recess 31 the guide pins 24 engage with their ends 26 a.
  • the ends 26 of the guide pins 24 are in FIG Fig. 2 Not shown.
  • a second recess 32 engages a projection 33 of the seal carrier 28 a. It follows immediately that not only a spoke truncation of the vane rings 11 and 12, but also a spoke centering of the seal carrier 28 of the so-called Outer Airseal seal takes place via the fork-shaped elements 27 and the guide pins 24 cooperating with the fork-shaped elements 27.
  • At least one non-illustrated stop is provided, wherein the or each stop is preferably integrated in one of the fork-shaped elements 27.
  • the or each stop limits the axial mobility of the vane rings 11 and 12 to a required minimum.
  • the guide pins 24 and bearing journals are, as already mentioned, associated with the housing 20 of the low-pressure turbine 10 and protrude with their free ends 26 into the interior of the low-pressure turbine 10.
  • the housing 20 holes are integrated for this purpose, wherein the bores are perpendicular to the housing 20.
  • the guide pins 24 are associated with nuts 34. When the nuts 34 are released, the guide pins 24 can move within the bores of the housing 20, whereas with the nuts 34 tightened, the guide pins 24, in particular the free ends 26 thereof, are fixed in their relative position to the housing 20.
  • the invention has been described using the example of a low-pressure turbine, it should again be noted that the invention can also be used in a compressor of a gas turbine. Preferred is the use of the invention in aircraft engines.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a turbomachine, in particular a gas turbine, according to the preamble of patent claim 1.

Turbomaschinen, zum Beispiel Gasturbinen, verfügen über einen Rotor und einen Stator, wobei der Rotor zusammen mit demselben rotierende Laufschaufeln und der Stator ein Gehäuse und Leitschaufeln aufweist. Die dem Rotor zugeordneten Laufschaufeln rotieren gegenüber dem feststehenden Gehäuse und den feststehenden Leitschaufeln des Stators. Die Leitschaufeln bilden Leitschaufelkränze und die Laufschaufeln bilden Laufschaufelkränze, wobei zwischen zwei in Durchströmungsrichtung hintereinander angeordneten Leitschaufelkränzen jeweils ein Laufschaufelkranz positioniert ist. Die Leitschaufelkränze grenzen mit einem radial außenliegenden Ende, insbesondere mit einem Außendeckbands, an das Gehäuse und mit einem radial innenliegenden Ende, insbesondere mit einem Innendeckband, an den Rotor an. Die Leitschaufelkränze sind am Gehäuse der Turbomaschine befestigt und können gegenüber dem Gehäuse speichenzentriert sein.Turbomachines, for example gas turbines, have a rotor and a stator, the rotor having a housing and vanes together with the same rotating blades and the stator. The blades associated with the rotor rotate with respect to the fixed housing and fixed stator vanes. The vanes form vane rings and the blades form rotor blade rings, wherein in each case a rotor blade ring is positioned between two guide vane rings arranged one behind the other in the flow direction. The Leitschaufelkränze border with a radially outer end, in particular with an outer shroud, to the housing and with a radially inner end, in particular with an inner shroud, to the rotor. The vane rings are attached to the housing of the turbomachine and may be memory centered with respect to the housing.

Das Dokument DE 198 07 247 A1 offenbart eine derartige Turbomaschine, wobei zur Zentrierung und Fixierung der Leitschaufelkränze Lagerzapfen vorgesehen sind. Gemäß diesem Dokument durchdringen die gehäusefesten Lagerzapfen das Gehäuse der Turbomaschine und greifen zur Speichenzentrierung der Leitschaufelkränze in den Leitschaufelkränzen zugeordnete Lagerbuchsen ein. Die Führungsstifte durchdringen dabei das Gehäuse der Turbomaschine in radialer Richtung, eine Längsmittelachse der Lagerbuchsen verläuft demnach parallel zur Radialrichtung der Turbomaschine, wobei die entsprechenden Lagerbuchsen ebenfalls in Radialrichtung der Turbomaschine ausgerichtet sind. Dabei sind zwischen zwei benachbarten Leitschaufelkränzen Dichtungsträger positioniert, wobei die Dichtungsträger in die Außendeckbänder der Leitschaufelkränze eingehängt sind.The document DE 198 07 247 A1 discloses such a turbomachine, wherein for the centering and fixing of the guide vane rings bearing journals are provided. According to this document, the housing-fixed journals penetrate the housing of the turbomachine and engage for the centering of the center of the vane rings in the guide vane rings associated bearing bushes. The guide pins penetrate the housing of the turbomachine in the radial direction, a longitudinal center axis of the bearing bushes thus runs parallel to the radial direction of the turbomachine, wherein the corresponding bearing bushes are also aligned in the radial direction of the turbomachine. In this case, seal carrier are positioned between two adjacent Leitschaufelkränzen, wherein the seal carrier are mounted in the outer shrouds of the Leitschaufelkränze.

Das Dokument US-A-2 801 075 schützt eine Turbomaschine mit Stator und Rotor, bei der mindestens ein Leitschaufelkranz gegenüber dem Gehäuse speichenzentriert ist, Dabei verlaufen das Gehäuse von außen durchdringende Lagerzapfen bzw. Führungsstifte etwa senkrecht zur Gehäusewand.The document US-A-2,801,075 protects a turbomachine with stator and rotor, in which at least one vane ring is memory-centered relative to the housing, while the housing extending from the outside penetrating bearing pins or guide pins approximately perpendicular to the housing wall.

Das Dokument US-A- 5 775 874 betrifft eine Turbomaschine mit Stator und Rotor, bei der mindestens ein Leitschaufelkranz aus mehreren Leitschaufelsegmenten zusammengesetzt ist. Jedes Leitschaufelsegment wird über eine U-förmige Klammer radial nach außen gegen das Gehäuse gespannt. Zusätzlich sind das Gehäuse von außen etwa senkrecht durchdringende Zapfen vorhanden, welche die Leitschaufelsegmente gegen ein Verdrehen in Umfangsrichtung sichern.The document U.S. Patent 5,775,874 relates to a turbomachine with stator and rotor, wherein at least one vane ring is composed of a plurality of vane segments. Each vane segment is stretched radially outwardly against the housing via a U-shaped bracket. In addition, the housing from the outside about perpendicularly penetrating pins are present, which secure the vane segments against rotation in the circumferential direction.

Das Dokument US-A-3 104 091 offenbart eine Turbomaschine mit Stator und Rotor, bei der mindestens ein Leitschaufelkranz gegenüber dm Gehäuse speichenzentriert ist. Dabei sind die Lagerzapfen bzw. Führungsstifte innerhalb des Gehäuses axial angeordnet.The document US-A-3 104 091 discloses a turbomachine with stator and rotor in which at least one vane ring is memory-centered with respect to the housing. The bearing pins or guide pins are arranged axially within the housing.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde eine neuartige Turbomaschine zu schaffen.On this basis, the present invention is based on the problem of providing a novel turbomachine.

Dieses Problem wird dadurch gelöst, dass die eingangs genannte Turbomaschine durch die Merkmale des kennzeichnenden Teils des Patentanspruchs 1 weitergebildet ist. In bekannter Weise verlaufen die Führungsstifte in etwa senkrecht zum Gehäuse, wobei in das Gehäuse hineinragende Enden der Führungsstifte in den radial außenliegenden Enden der Leitschaufelkränze zugeordnete, gabelförmige Elemente eingreifen. Erfindungsgemäß sind sowohl die Leitschaufelkränze als auch Dichtungsträger mit Hilfe der Führungsstifte und der gabelförmigen Elemente speichenzentriert.This problem is solved in that the above-mentioned turbomachine is further developed by the features of the characterizing part of patent claim 1. In a known manner, the guide pins extend approximately perpendicular to the housing, wherein projecting into the housing ends of the guide pins in the radially outer ends of the guide vane rings associated, fork-shaped elements engage. According to the invention, both the guide vane rings and the seal carrier are memory-centered by means of the guide pins and the fork-shaped elements.

Jedes gabelförmige Element begrenzt vorzugsweise mindestens zwei Ausnehmungen bzw. Aufnahmeräume, wobei die Führungsstifte in eine erste Ausnehmung und wobei Vorsprünge der Dichtungsträger in eine zweite Ausnehmung eingreifen. Die beiden Ausnehmungen der gabelförmige Elemente sind in Umfangrichtung nebeneinander positioniert.Each fork-shaped element preferably defines at least two recesses or receiving spaces, wherein the guide pins engage in a first recess and wherein projections of the seal carrier engage in a second recess. The two recesses of the fork-shaped elements are positioned next to each other in the circumferential direction.

Bei einem sich verjüngenden oder erweiternden Gehäuse, z. B. mit konischer Gehäusewand, verlaufen die Führungsstifte demnach nicht in radialer Richtung der Turbomaschine, sondern einerseits schräg zur Radialrichtung und andererseits schräg zur Axialrichtung der Turbomaschine. In das Gehäuse hineinragende Enden der Führungsstifte verlaufen demnach ebenfalls schräg zur Axialrichtung sowie Radialrichtung der Turbomaschine und wirken mit gabelförmigen Elementen im Bereich der Leitschaufelkränze zusammen, wobei die gabelförmigen Elemente in Radialrichtung und Axialrichtung der Turbomaschine zumindest teilweise offen ausgebildet sind, um ein Eingreifen der in das Gehäuse hineinragenden Enden der Führungsstifte in die gabelförmigen Elemente zu ermöglichen.In a tapered or widening housing, z. B. conical housing wall, the guide pins therefore do not extend in the radial direction of the turbomachine, but on the one hand obliquely to the radial direction and on the other hand obliquely to the axial direction of the turbomachine. In the housing projecting ends of the guide pins thus also extend obliquely to the axial direction and radial direction of the turbomachine and cooperate with fork-shaped elements in the vane rings, the fork-shaped elements in the radial direction and axial direction of the turbomachine are at least partially open, to intervene in the Casing projecting ends of the guide pins in the fork-shaped elements to allow.

Mithilfe der erfindungsgemäßen Konstruktion ist eine einfachere Ausführung des Gehäuses der Turbomaschine möglich, da auf gehäuseseitige, in Radialrichtung verlaufende Führungshülsen für die Lagerzapfen bzw. Führungsstifte verzichtet werden kann. Dies erlaubt eine deutlich einfachere Herstellung des Gehäuses und reduziert damit die Herstellkosten der Turbomaschine.By means of the construction according to the invention, a simpler design of the housing of the turbomachine is possible because the housing-side, extending in the radial direction guide sleeves for the bearing pins or guide pins are dispensed with can. This allows a much simpler production of the housing and thus reduces the manufacturing costs of the turbomachine.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den abhängigen Unteransprüchen und der nachfolgenden Beschreibung.Preferred embodiments of the invention will become apparent from the dependent subclaims and the following description.

Ein Ausführungsbeispiel der Erfindung wird, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. In der Zeichnung zeigt:

Fig. 1:
einen teilweisen axialen Querschnitt durch eine erfindungsgemäße Gasturbine; und
Fig. 2:
ein stark schematisiertes Detail der Anordnung gemäß Fig. 1 im Bereich eines Außendeckbands eines Leitschaufelgitters und einer "Outer Airseal" Dichtung in perspektivischer Ansicht.
An embodiment of the invention will be described, without being limited thereto, with reference to the drawing. In the drawing shows:
Fig. 1:
a partial axial cross section through a gas turbine according to the invention; and
Fig. 2:
a highly schematic detail of the arrangement according to Fig. 1 in the area of an outer shroud of a guide vane grille and an "Outer Airseal" seal in perspective view.

Nachfolgend wird die hier vorliegende Erfindung unter Bezugnahme auf Fig. 1 und 2 in größerem Detail beschrieben. Bevor auf die Details des bevorzugten Ausführungsbeispiels eingegangen wird, soll angemerkt werden, dass die vorliegende Erfindung generell für alle Strömungsmaschinen bzw. Turbomaschinen mit Rotor und Stator geeignet ist. Insbesondere eignet sich die Erfindung zur Anwendung in einem Verdichter oder einer Turbine einer Gasturbine, insbesondere eines Flugtriebwerks. Thermodynamisch und abmessungsbedingt sind Niederdruckturbinen mittlerer bis großer Gasturbinen bevorzugte Anwendungsfälle der hier vorliegenden Erfindung, weshalb Fig. 1 einen teilweisen, axialen Längsschnitt durch eine Niederdruckturbine zeigt.Hereinafter, the present invention will be described with reference to FIG Fig. 1 and 2 described in more detail. Before going into the details of the preferred embodiment, it should be noted that the present invention is generally suitable for all turbomachinery with rotor and stator. In particular, the invention is suitable for use in a compressor or a turbine of a gas turbine, in particular an aircraft engine. Thermodynamic and dimensional reasons, low-pressure turbines medium to large gas turbines are preferred applications of the present invention, which is why Fig. 1 a partial, axial longitudinal section through a low-pressure turbine shows.

Fig. 1 zeigt einen Ausschnitt aus einer Niederdruckturbine 10 im Bereich von zwei Leitschaufelkränzen 11 und 12 sowie zwei Laufschaufelkränzen 13 und 14. Die Leit schaufelkränze 11 und 12 sowie Laufschaufelkränze 13 und 14 sind in axialer Richtung der Niederdruckturbine 10 wechselweise hintereinander positioniert. Die Axialrichtung der Niederdruckturbine 10 ist in Fig. 1 durch einen Pfeil 15 dargestellt, die Radialrichtung derselben durch einen Pfeil 16. Fig. 1 shows a section of a low-pressure turbine 10 in the range of two vane rings 11 and 12 and two blade rings 13 and 14. Die Leit Blade rings 11 and 12 and blade rings 13 and 14 are alternately positioned one behind the other in the axial direction of the low-pressure turbine 10. The axial direction of the low-pressure turbine 10 is in Fig. 1 represented by an arrow 15, the radial direction thereof by an arrow 16th

Jeder der Leitschaufelkränze 11 und 12 wird durch mehrere in Umfangsrichtung der Niederdruckturbine 10 nebeneinander angeordnete Leitschaufeln 17 gebildet, wobei Fig. 1 lediglich die radial außenliegenden Enden 18 der Leitschaufeln 17 zeigt. Im Bereich der radial außenliegenden Enden 18 der Leitschaufeln 17 sind sogenannte Außendeckbänder 19 ausgebildet. Die Leitschaufelkränze 11 und 12 sind einem Stator der Niederdruckturbine 10 zugeordnet, wobei der Stator neben den Leitschaufeln 17 der Leitschaufelkränze 11 und 12 auch ein Gehäuse 20 umfasst. Das Gehäuse 20 sowie die Leitschaufelkränze 11 und 12 sind feststehend ausgebildet, wobei die einem Rotor zugeordneten Laufschaufelkränze 13 und 14 gegenüber den feststehenden Leitschaufelkränzen 11 und 12 sowie dem feststehenden Gehäuse 20 rotieren. Jeder der rotierenden Laufschaufelkränze 13 und 14 wird dabei von mehreren in Umfangsrichtung der Niederdruckturbine 10 nebeneinander angeordneten Laufschaufeln 21 gebildet, wobei Fig. 1 wiederum nur die radial außenliegenden Enden 22 der Laufschaufeln 21 zeigt. Im Bereich der radial außenliegenden Enden 22 der Laufschaufeln 21 sind jeweils wiederum sogenannte Außendeckbänder 23 ausgebildet.Each of the vane rings 11 and 12 is formed by a plurality of circumferentially of the low-pressure turbine 10 juxtaposed vanes 17, wherein Fig. 1 only the radially outer ends 18 of the vanes 17 shows. In the region of the radially outer ends 18 of the guide vanes 17 so-called outer shrouds 19 are formed. The vane rings 11 and 12 are associated with a stator of the low-pressure turbine 10, wherein the stator in addition to the vanes 17 of the vane rings 11 and 12 and a housing 20 includes. The housing 20 and the vane rings 11 and 12 are fixed, wherein the rotor blades associated with a rotor blades 13 and 14 with respect to the fixed vane rings 11 and 12 and the fixed housing 20 rotate. Each of the rotating blade rings 13 and 14 is thereby formed by a plurality of circumferentially of the low-pressure turbine 10 juxtaposed blades 21, wherein Fig. 1 again only the radially outer ends 22 of the blades 21 shows. In the area of the radially outer ends 22 of the rotor blades 21, in each case so-called outer shrouds 23 are formed in turn.

Im Sinne der hier vorliegenden Erfindung erfolgt die Zentrierung und Fixierung der Leitschaufelkränze 11 und 12 über Lagerzapfen bzw. Führungsstifte 24, wobei die Führungsstifte 24 in etwa senkrecht zum Gehäuse 20 verlaufen. Wie Fig. 1 entnommen werden kann, steht eine Längsmittelachse 25 der Führungsstifte 24 in etwa senkrecht auf dem Gehäuse 20 und verläuft demnach schräg zur Radialrichtung (Pfeil 16) sowie Axialrichtung (Pfeil 15) der Niederdruckturbine 10. Mit Enden 26 ragen die Führungsstifte 24 in das Gehäuse 20 hinein und greifen dabei zur Zentrierung und Fixierung der Leitschaufelkränze 11 und 12 in gabelförmige Elemente 27 ein, die den Außendeckbändern 19 der Leitschaufelkränze 11 und 12 zugeordnet sind. Über den Umfang der Außendeckbänder der Leitschaufelkränze 11 und 12 sind dabei mehrere gabelförmige Elemente 27 positioniert, wobei in jedes der gabelförmigen Elemente 27 eines Leitschaufelkranzes 11 bzw. 12 ein entsprechender Führungsstift 24 eingreift, wobei die Führungsstifte 24 entsprechend zu den gabelförmigen Elementen 27 über den Umfang des Gehäuses verteilt angeordnet sind. Zur Speichenzentrierung eines Leitschaufelkranzes 11 bzw. 12 sind mindestens drei über den Umfang der Niederdruckturbine 10 verteilt angeordnete Führungsstifte 24 erforderlich, die mit entsprechenden gabelförmigen Elementen 27 im Bereich der Außendeckbänder 19 der Leitschaufelkränze 11 und 12 zusammenwirken. Bevorzugt sind je Leitschaufelkranz 11 und 12 sieben derartige Paare aus Führungsstiften 24 und gabelförmigen Elementen 27 über den Umfang der Niederdruckturbine 10 verteilt angeordnet.For the purposes of the present invention, the centering and fixing of the vane rings 11 and 12 via bearing pins or guide pins 24 takes place, wherein the guide pins 24 extend approximately perpendicular to the housing 20. As Fig. 1 can be removed, is a longitudinal central axis 25 of the guide pins 24 approximately perpendicular to the housing 20 and thus extends obliquely to the radial direction (arrow 16) and axial direction (arrow 15) of the low-pressure turbine 10. With ends 26 protrude the guide pins 24 into the housing 20 and thereby engage for centering and fixing the guide vane rings 11 and 12 in fork-shaped elements 27, which are the outer shrouds 19 of the vane rings 11 and 12 associated. A plurality of fork-shaped elements 27 are positioned over the circumference of the outer shrouds of the guide vane rings 11 and 12, wherein in each of the fork-shaped elements 27 of a guide vane ring 11 and 12, a corresponding guide pin 24 engages, wherein the guide pins 24 are arranged distributed according to the fork-shaped elements 27 over the circumference of the housing. For centering of a vane ring 11 and 12 at least three distributed over the circumference of the low pressure turbine 10 arranged guide pins 24 are required, which cooperate with corresponding fork-shaped elements 27 in the region of the outer shrouds 19 of the guide vane rings 11 and 12. Preferably, per guide vane ring 11 and 12 seven such pairs of guide pins 24 and fork-shaped elements 27 are arranged distributed over the circumference of the low-pressure turbine 10.

Die gabelförmigen Elemente 27 im Bereich der Außendeckbänder 19 der Leitschaufelkränze 11 und 12 sind in Radialrichtung sowie in Axialrichtung der Niederdruckturbine 10 zumindest teilweise offen, um ein Eingreifen der in das Gehäuse 20 hineinragenden Enden 26 der Führungsstifte 24 in die gabelförmigen Elemente 27 zu ermöglichen.The fork-shaped elements 27 in the region of the outer shrouds 19 of the Leitschaufelkränze 11 and 12 are at least partially open in the radial direction and in the axial direction of the low-pressure turbine 10 to allow engagement of the projecting into the housing 20 ends 26 of the guide pins 24 in the fork-shaped elements 27.

Im Sinne der hier vorliegenden Erfindung bewirken die gabelförmigen Elemente 27 der Leitschaufelkränze 11 und 12 zusammen mit den Führungsstiften 24 nicht lediglich eine Fixierung und Zentrierung der Leitschaufelkränze 11 und 12 am Gehäuse, sondern vielmehr auch eine Fixierung und Zentrierung von Dichtungsträgern 28, die zwischen benachbarten Außendeckbändern 18 benachbarter Leitschaufelkränze 11 und 12 angeordnet sind. Die Dichtungsträger 28 tragen im gezeigten Ausführungsbeispiel als Wabendichtungen ausgebildete Dichtkörper 29, die mit sogenannten Dichtfins 30 im Bereich der Außendeckbänder 23 der Laufschaufelkränze 13 und 14 zusammenwirken und eine Abdichtung eines Spalts zwischen den radial außenliegenden Enden 22 der Laufschaufeln 21 und dem Gehäuse 20 der Niederdruckturbine 10 bewirken.For the purposes of the present invention, the fork-shaped elements 27 of the vane rings 11 and 12 together with the guide pins 24 not only fixation and centering of the vane rings 11 and 12 on the housing, but also a fixation and centering of seal carriers 28, between adjacent outer shrouds 18 adjacent vane rings 11 and 12 are arranged. The seal carrier 28 carry in the embodiment shown as a honeycomb seals sealing body 29, which cooperate with so-called sealing fins 30 in the outer shrouds 23 of the blade rings 13 and 14 and a seal of a gap between the radially outer ends 22 of the blades 21 and the housing 20 of the low-pressure turbine 10th cause.

Die Dichtungsträger 28 greifen ebenso wie die Führungsstifte 24 in die gabelförmigen Elemente 27 im Bereich der Außendeckbänder 19 der Leitschaufelkränze 11 und 12 ein. Dies kann insbesondere Fig. 2 entnommen werden. So zeigt Fig. 2 ein gabelförmiges Element 27 im Bereich eines Außendeckbands 19 eines Leitschaufelkranzes sowie einen Abschnitt eines Dichtungsträgers 28, der ein e sogenannte Outer Airseal-Dichtung bildet. Das gabelförmige Element 27 verfügt über zwei Ausnehmungen 31 und 32. Die beiden Ausnehmungen 31 und 32 sind sowohl in Radialrichtung als auch in Axialrichtung der Niederdruckturbine 10 teilweise offen und in Umfangsrichtung derselben nebeneinander angeordnet. In eine erste Ausnehmung 31 greifen die Führungsstifte 24 mit ihren Enden 26 ein. Aus Gründen einer übersichtlicheren Darstellung sind die Enden 26 der Führungsstifte 24 in Fig. 2 nicht gezeigt. In eine zweite Ausnehmung 32 greift ein Vorsprung 33 des Dichtungsträgers 28 ein. Daraus folgt unmittelbar, dass über die gabelförmigen Elemente 27 und die mit den gabelförmigen Elementen 27 zusammenwirkenden Führungsstifte 24 nicht nur eine Speichenzentrlerung der Leitschaufelkränze 11 und 12, sondern vielmehr auch eine Speichenzentrierung der Dichtungsträger 28 der sogenannter Outer Airseal-Dichtung erfolgt.The seal carrier 28 as well as the guide pins 24 engage in the fork-shaped elements 27 in the region of the outer shrouds 19 of the Leitschaufelkränze 11 and 12 a. This can be special Fig. 2 be removed. So shows Fig. 2 a fork-shaped element 27 in the region of an outer shroud 19 of a vane ring and a portion of a seal carrier 28, which is a so-called Outer Airseal seal forms. The fork-shaped element 27 has two recesses 31 and 32. The two recesses 31 and 32 are partially open both in the radial direction and in the axial direction of the low-pressure turbine 10 and in the circumferential direction of the same side by side. In a first recess 31, the guide pins 24 engage with their ends 26 a. For clarity, the ends 26 of the guide pins 24 are in FIG Fig. 2 Not shown. In a second recess 32 engages a projection 33 of the seal carrier 28 a. It follows immediately that not only a spoke truncation of the vane rings 11 and 12, but also a spoke centering of the seal carrier 28 of the so-called Outer Airseal seal takes place via the fork-shaped elements 27 and the guide pins 24 cooperating with the fork-shaped elements 27.

Um eine Beweglichkeit der Leitschaufelkränze 11 und 12 in Axialrichtung der Niederdruckturbine 10 zu begrenzen, ist mindestens ein nicht-dargestellter Anschlag vorgesehen, wobei der oder jeder Anschlag vorzugsweise in eines der gabelförmigen Elemente 27 integriert ist. Durch den oder jeden Anschlag wird die axiale Beweglichkeit der Leitschaufelkränze 11 und 12 auf ein erforderliches Minimum begrenzt.In order to limit the mobility of the vane rings 11 and 12 in the axial direction of the low-pressure turbine 10, at least one non-illustrated stop is provided, wherein the or each stop is preferably integrated in one of the fork-shaped elements 27. The or each stop limits the axial mobility of the vane rings 11 and 12 to a required minimum.

Die Führungsstifte 24 bzw. Lagerzapfen sind, wie bereits erwähnt, dem Gehäuse 20 der Niederdruckturbine 10 zugeordnet und ragen mit ihren freien Enden 26 in das Innere der Niederdruckturbine 10 hinein. In das Gehäuse 20 sind hierzu Bohrungen integriert, wobei die Bohrungen senkrecht zum Gehäuse 20 verlaufen. Auf der Außenseite des Gehäuses 20 sind den Führungsstiften 24 Muttern 34 zugeordnet. Bei gelösten Muttern 34 können sich die Führungsstifte 24 innerhalb der Bohrungen des Gehäuses 20 bewegen, wohingegen bei festgezogenen Muttern 34 die Führungsstifte 24, insbesondere die freien Enden 26 derselben, in ihrer Relativposition zum Gehäuse 20 festgestellt sind.The guide pins 24 and bearing journals are, as already mentioned, associated with the housing 20 of the low-pressure turbine 10 and protrude with their free ends 26 into the interior of the low-pressure turbine 10. In the housing 20 holes are integrated for this purpose, wherein the bores are perpendicular to the housing 20. On the outside of the housing 20, the guide pins 24 are associated with nuts 34. When the nuts 34 are released, the guide pins 24 can move within the bores of the housing 20, whereas with the nuts 34 tightened, the guide pins 24, in particular the free ends 26 thereof, are fixed in their relative position to the housing 20.

Obwohl im obigen Ausführungsbeispiel die Erfindung am Beispiel einer Niederdruckturbine beschrieben wurde, sei nochmals darauf hingewiesen, dass die Erfindung auch bei einem Verdichter einer Gasturbine Verwendung finden kann. Bevorzugt ist die Verwendung der Erfindung bei Flugtriebwerken.Although in the above embodiment, the invention has been described using the example of a low-pressure turbine, it should again be noted that the invention can also be used in a compressor of a gas turbine. Preferred is the use of the invention in aircraft engines.

Claims (9)

  1. A turbomachine, in particular a gas turbine, having a stator and a rotor, wherein the rotor has rotor blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide-vane rings (11, 12) which with radially external ends (18) are adjacent to the housing (20) and with radially internal ends are adjacent to the rotor, wherein the guide-vane rings are centred in a spoke-like manner with the aid of bearing journals or guide pins (24) associated with the housing (20) and penetrating the housing (20), wherein the guide pins (24) extend substantially perpendicularly to the housing (20), wherein ends (26) of the guide pins (24), projecting into the housing, engage associated fork-shaped elements (27) in the radially external ends (18) of the guide-vane rings (11, 12), characterised in that seal-carriers (28) are arranged between the radially external ends (18) of the guide vanes (17) of adjacent guide-vane rings (11, 12), and wherein the seal-carriers (28) are arranged between outer shrouds (19) of adjacent guide-vane rings (11, 12), and radially external ends of the rotor blades (21) cooperate with sealing bodies (29) associated with the seal-carriers (28), wherein both the guide-vane rings (11, 12) and the seal-carriers (28) are centred in a spoke-like manner with the aid of the guide pins (24) and the fork-shaped elements (27).
  2. A turbomachine according to claim 1, characterised in that the guide pins (24) extend substantially perpendicularly to the housing and obliquely to the radial direction and also the axial direction of the turbomachine.
  3. A turbomachine according to claim 1 or 2, characterised in that the fork-shaped elements (27) are at least in part open in the radial direction and axial direction of the turbomachine.
  4. A turbomachine according to one of claims 1 to 3, characterised in that the fork-shaped elements (27) are associated with an outer shroud (19) of the guide-vane rings.
  5. A turbomachine according to one of claims 1 to 4, characterised in that a plurality of fork-shaped elements (27) are positioned so as to be distributed over the circumference of a guide-vane ring (11, 12), wherein a plurality of guide pins (24) that are positioned so as to be distributed over the circumference of the housing (20) engage into the fork-shaped elements (27).
  6. A turbomachine according to one of claims 1 to 5, characterised in that the fork-shaped elements (27) delimit at least two recesses (31, 32), wherein the guide pins (24) engage into a first recess (31), and wherein projections (33) of the seal-carriers (28) engage into a second recess (32).
  7. A turbomachine according to claim 6, characterised in that the recesses (31, 32) of the fork-shaped elements (27) are positioned next to one another in the circumferential direction.
  8. A turbomachine according to one of claims 1 to 7, characterised by at least one stop for delimitation of the axial displaceability of the guide-vane rings (11, 12).
  9. A turbomachine according to claim 8, characterised in that the or each stop is integrated into at least one of the fork-shaped elements (27).
EP04802843.5A 2003-12-19 2004-11-27 Turbomachine Expired - Lifetime EP1694943B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10359730A DE10359730A1 (en) 2003-12-19 2003-12-19 Turbomachine, in particular gas turbine
PCT/DE2004/002634 WO2005059312A2 (en) 2003-12-19 2004-11-27 Turbomachine, especially a gas turbine

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EP1694943A2 EP1694943A2 (en) 2006-08-30
EP1694943B1 true EP1694943B1 (en) 2013-05-29

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US (1) US7704042B2 (en)
EP (1) EP1694943B1 (en)
CA (1) CA2548489A1 (en)
DE (1) DE10359730A1 (en)
WO (1) WO2005059312A2 (en)

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EP1694943A2 (en) 2006-08-30
CA2548489A1 (en) 2005-06-30
US20070122270A1 (en) 2007-05-31
WO2005059312A3 (en) 2005-09-01
US7704042B2 (en) 2010-04-27
WO2005059312A2 (en) 2005-06-30
DE10359730A1 (en) 2005-07-14

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