EP1673519A1 - Sealing arrangement for a gas turbine - Google Patents

Sealing arrangement for a gas turbine

Info

Publication number
EP1673519A1
EP1673519A1 EP04786886A EP04786886A EP1673519A1 EP 1673519 A1 EP1673519 A1 EP 1673519A1 EP 04786886 A EP04786886 A EP 04786886A EP 04786886 A EP04786886 A EP 04786886A EP 1673519 A1 EP1673519 A1 EP 1673519A1
Authority
EP
European Patent Office
Prior art keywords
sealing
rotor
guide vane
sealing arrangement
arrangement according
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
EP04786886A
Other languages
German (de)
French (fr)
Other versions
EP1673519B1 (en
Inventor
Marcello De Martino
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
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 filed Critical MTU Aero Engines GmbH
Publication of EP1673519A1 publication Critical patent/EP1673519A1/en
Application granted granted Critical
Publication of EP1673519B1 publication Critical patent/EP1673519B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Definitions

  • the invention relates to a sealing arrangement for a gas turbine according to the preamble of patent claim 1.
  • Gas turbines consist of several assemblies, for example a fan, a combustion chamber, preferably several compressors and several turbines.
  • the preferably several turbines are in particular a high-pressure turbine and a low-pressure turbine, and the several compressors are in particular a high-pressure compressor and a low-pressure compressor.
  • a plurality of guide vane rings are positioned one behind the other in a turbine and a compressor of a gas turbine in the axial direction or in the flow direction of the gas turbine, each guide vane ring having a plurality of guide vanes which are arranged distributed over the circumference.
  • a rotor blade ring which has a plurality of rotor blades, is positioned between each two adjacent guide vane rings. The rotor blades are assigned to a rotor and rotate together with the rotor with respect to a fixed housing and also the guide vanes of the guide vane rings, which are also designed to be stationary.
  • sealing arrangements are known from the prior art which serve to seal a gap between the radially inner ends of the fixed guide vanes and the rotor of the gas turbine, these sealing arrangements being designed in this way are that the rotor has at least two sealing projections which run in the circumferential direction of the rotor and are positioned at an axial distance from one another and which interact with inlet linings which are assigned to the radially inner ends of the fixed guide vanes.
  • the present invention relates to a sealing arrangement for sealing the gap between radially inner ends of the guide blades of a guide blade ring and a rotor of the gas turbine.
  • the present invention is based on the problem of creating a novel sealing arrangement for a gas turbine.
  • the sealing projections are inclined or inclined in the axial direction towards a side of higher pressure, at least one recirculation structure being arranged in a space delimited by the at least two sealing projections and the corresponding inlet linings, and the or each recirculation structure being on the side of higher pressure is aligned.
  • the sealing projections are designed as sealing fins and the inlet linings as honeycomb structures.
  • the sealing projections interacting with a guide vane ring and the corresponding inlet linings of the guide vane ring preferably have different radii, with outer radii of the sealing projections and inner radii of the inlet linings increasing or increasing in the direction of the side of higher pressure.
  • FIG. 1 shows a schematic cross section through a compressor 10 of a gas turbine with a fixed housing 11 and a rotor 12 rotating relative to the fixed housing 11, the fixed housing 11 and the rotor 12 delimiting a main flow channel 13.
  • the direction of flow through the main flow channel 13 is visualized in FIG. 1 by an arrow 14.
  • a plurality of stationary guide vane rings 15 are arranged one behind the other in the main flow channel 13 in the axial direction or in the flow direction, FIG. 1 only showing such a guide vane ring 15.
  • Each guide vane ring 15 is formed by a plurality of guide vanes 16 which are arranged around the rotor 12 at an axial position of the compressor 10 in the circumferential direction thereof.
  • the fixed guide vanes 16 are integrated into the housing 11 with a radially outer end 17.
  • a gap 19 is formed between a radially inner end 18 of the guide vanes 16 opposite the radially outer end 17 and the rotor 12.
  • a rotor blade ring is arranged between two adjacent, stationary guide vane rings 15. 1 shows such a rotor blade ring 20, which is formed from a plurality of rotor blades 21 which are fastened to the rotor 12 with a radially inner end 22. Again, a gap is formed between a radially outer end 23 of the blades 21 and the housing 11 of the compressor 10. To seal this radial gap between the radially outer ends 23 of the rotating blades 20 and the fixed gear Housing 1 1 is assigned to housing 1 1, a so-called run-in coating 24, which enables the radially outer ends 23 of rotor blades 21 to be rubbed against housing 1 1 of compressor 10 with little wear.
  • the present invention relates to a sealing arrangement for sealing the gap 19 between the radially inner ends 18 of the stationary guide vanes 16 of a guide vane ring 15 and the rotor 12 of the compressor 10.
  • this sealing arrangement comprises two associated with the rotor 12 Sealing protrusions 25 and 26.
  • the sealing projections 25 and 26 are designed as so-called sealing fins and are spaced apart from one another in the axial direction of the compressor 10.
  • the sealing projections 25 and 26 extend over the entire circumference of the rotor 12, that is to say they are closed in the circumferential direction.
  • the sealing projections 25 and 26 cooperate with inlet linings 27 and 28.
  • the inlet linings 27 and 28 are assigned to the radially inner ends 18 of the fixed guide vanes 16, namely integrated into the radially inner ends 18 of the guide vanes 16 designed as a platform.
  • the inlet linings 27 and 28 are accordingly designed to be stationary and the sealing projections 25 and 26 rotate together with the rotor 12 relative to the stationary inlet linings 27 and 28.
  • the inlet linings 27 and 28 are preferably designed as honeycomb seals, with honeycombs of these honeycomb structures in the direction of the sealing projections 25 and 26 are open.
  • the gas pressure inside the compressor increases in the direction of flow (arrow 14).
  • the sealing projections 25 and 26, which - as already mentioned - are designed as sealing fins, are inclined or inclined in the axial direction towards a side of higher gas pressure.
  • FIG. 1 shows that the flow direction of the main flow channel 13 of the compressor 10 runs from left to right, that is to say a gas pressure on the right side of the guide vanes 16 is higher than on the left side of the latter.
  • the sealing projections 25 and 26 are with their tips to the right side, that is to the side higher gas pressure, inclined. This optimizes the sealing effect of the sealing projections 25 and 26.
  • a recirculation structure 30 is arranged in a space 29 delimited by the sealing projections 25 and 26 and the corresponding inlet linings 27 and 28.
  • the recirculation structure 30 is integrated into the radially inner end 18 of the guide vanes 16 of the guide vane ring 15, the radially inner ends 18 being designed as a platform for the guide vanes 16.
  • the inlet linings 27 and 28, which are also assigned to the radially inner end 18 of the guide vanes 16, are arranged on both sides of the recirculation structure 30 according to FIG. 1. It is within the meaning of the present invention that the recirculation structure 30, like the sealing projections 25 and 26, is oriented towards the side of higher gas pressure.
  • the sealing effect is further optimized by integrating a recirculation structure 30 designed in this way into the sealing arrangement comprising sealing projections 25 and 26 and corresponding inlet linings 27 and 28.
  • the two sealing projections 25 and 26 and the two inlet linings 27 and 28 interacting with the sealing projections 25 and 26 have stepped radii.
  • the sealing protrusion 26 located downstream in the direction of flow (arrow 14), which in the case of a compressor is accordingly arranged on the side of higher gas pressure than the upstream sealing protrusion 25, has an outer radius that is larger than that of the upstream sealing protrusion 25.
  • the inlet lining 28 cooperating with the downstream sealing projection 26 also has a larger inner diameter than the inlet lining 27 interacting with the upstream sealing projection 25.
  • the recirculation structure 30 projects radially beyond the downstream inlet lining 28.
  • each guide vane ring 15 is shown in the schematic representation according to FIG. 1, a plurality of such guide vane rings are positioned one behind the other in the compressor 10 in the axial direction.
  • Each guide vane ring can have a sealing arrangement as described above for sealing the radial gap 19 between the radially inner ends 18 of the fixed guide vanes and the rotor 12.
  • the present invention is preferably used to reduce the leakage in the so-called statorwell cavities of high-pressure compressors of an aircraft engine.
  • the sealing arrangement according to the invention can also be used in the turbines of aircraft engines or in stationary gas turbines.

Landscapes

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

Abstract

The sealing arrangement serves to seal off a gap (19) between the radially inner lying ends (18) of the guide blades (16) of a vane ring (15) and a rotor (12), wherein the rotor (12) has at least two sealing protrusions (25, 26) extending in peripheral direction of the rotor (12) and positioned at an axial distance with respect to one another, which, combined with inlet linings (27, 28) assigned to the radially inner-lying ends (18) of the guide blades (16), form a sealing of the gap (19). According to the invention, the sealing protrusions (25, 26) are inclined or slanted in axial direction towards a side having a higher pressure, wherein at least one recirculation structure (30) is arranged in an area (29) defined by the at least two sealing protrusions (25, 26) and the corresponding inlet linings (27, 28) and wherein the recirculation structure(s) (30) are aligned towards the side having a higher pressure.

Description

Dichtungsanordnung für eine Gasturbine Sealing arrangement for a gas turbine
Die Erfindung betrifft eine Dichtungsanordnung für eine Gasturbine nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a sealing arrangement for a gas turbine according to the preamble of patent claim 1.
Gasturbinen bestehen aus mehreren Baugruppen, so zum Beispiel unter anderem aus einem Lüfter (Fan), einer Brennkammer, vorzugsweise mehreren Verdichtern sowie mehreren Turbinen. Bei den vorzugsweise mehreren Turbinen handelt es sich insbesondere um eine Hochdruckturbine sowie eine Niederdruckturbine, bei den mehreren Verdichtern insbesondere um einen Hochendruckverdichter sowie Niederdruckverdichter.Gas turbines consist of several assemblies, for example a fan, a combustion chamber, preferably several compressors and several turbines. The preferably several turbines are in particular a high-pressure turbine and a low-pressure turbine, and the several compressors are in particular a high-pressure compressor and a low-pressure compressor.
In einer Turbine sowie einem Verdichter einer Gasturbine sind in axialer Richtung bzw. in Durchströmungsrichtung der Gasturbine hintereinander mehrere Leitschaufelkränze positioniert, wobei jeder Leitschaufelkranz mehrere, über den Umfang verteilt angeordnete Leitschaufeln aufweist. Zwischen jeweils zwei benachbarten Leitschaufelkränzen ist jeweils ein Laufschaufelkranz positioniert, der mehrere Laufschaufeln aufweist. Die Laufschaufeln sind einem Rotor zugeordnet und rotieren zusammen mit dem Rotor gegenüber einem feststehenden Gehäuse sowie den ebenfalls feststehend ausgebildeten Leitschaufeln der Leitschaufelkränze.A plurality of guide vane rings are positioned one behind the other in a turbine and a compressor of a gas turbine in the axial direction or in the flow direction of the gas turbine, each guide vane ring having a plurality of guide vanes which are arranged distributed over the circumference. A rotor blade ring, which has a plurality of rotor blades, is positioned between each two adjacent guide vane rings. The rotor blades are assigned to a rotor and rotate together with the rotor with respect to a fixed housing and also the guide vanes of the guide vane rings, which are also designed to be stationary.
Zur Optimierung des Wirkungsgrads einer Gasturbine müssen Leckagen einerseits zwischen den rotierenden Laufschaufeln und dem feststehenden Gehäuse und andererseits zwischen den feststehenden Leitschaufeln und dem Rotor durch effektive Dichtungssysteme vermieden werden. So ist es aus dem Stand der Technik bereits bekannt, zur Abdichtung eines Spalts zwischen den radial außenliegenden Enden der Laufschaufeln und dem feststehenden Gehäuse spezielle Einlaufbeläge zu verwenden, wobei die Einlaufbeläge auf dem feststehenden Gehäuse aufgebracht sind, um ein verschleißfreies Anstreifen der radial außenliegenden Enden der rotierenden Laufschaufeln in den Einlaufbelag zu ermöglichen. Des weiteren sind aus dem Stand der Technik Dichtungsanordnungen bekannt, die der Abdichtung eines Spalts zwischen den radial innenliegenden Enden der feststehenden Leitschaufeln und dem Rotor der Gasturbine dienen, wobei diese Dichtungsanordnungen derart ausgestaltet sind, dass der Rotor mindestens zwei in Umfangsrichtung des Rotors verlaufende, mit axialem Abstand zueinander positionierte Dichtungsvorsprünge aufweist, die mit Einlaufbelägen zusammenwirken, die den radial innenliegenden Enden der feststehenden Leitschaufeln zugeordnet sind.In order to optimize the efficiency of a gas turbine, leaks between the rotating blades and the fixed housing and, on the other hand, between the fixed guide vanes and the rotor must be avoided by effective sealing systems. Thus, it is already known from the prior art to use special inlet linings to seal a gap between the radially outer ends of the rotor blades and the fixed housing, the inlet linings being applied to the fixed housing in order to ensure that the radially outer ends of the rotor are not subject to wear to allow rotating blades in the inlet surface. Furthermore, sealing arrangements are known from the prior art which serve to seal a gap between the radially inner ends of the fixed guide vanes and the rotor of the gas turbine, these sealing arrangements being designed in this way are that the rotor has at least two sealing projections which run in the circumferential direction of the rotor and are positioned at an axial distance from one another and which interact with inlet linings which are assigned to the radially inner ends of the fixed guide vanes.
Die hier vorliegende Erfindung betrifft eine Dichtungsanordnung zur Abdichtung des Spalts zwischen radial innenliegenden Enden der Leitschaufeln eines Leitschaufelkranzes und einem Rotor der Gasturbine.The present invention relates to a sealing arrangement for sealing the gap between radially inner ends of the guide blades of a guide blade ring and a rotor of the gas turbine.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Dichtungsanordnung für eine Gasturbine zu schaffen.Proceeding from this, the present invention is based on the problem of creating a novel sealing arrangement for a gas turbine.
Dieses Problem wird dadurch gelöst, dass die eingangs genannte Dichtungsanordnung durch die Merkmale des kennzeichnenden Teils des Patentanspruchs 1 weitergebildet ist. Erfindungsgemäß sind die Dichtungsvorsprünge in axialer Richtung zu einer Seite höheren Drucks hin geneigt bzw. schräggestellt, wobei in einem von den mindestens zwei Dichtungsvorsprüngen und den entsprechenden Einlaufbelägen begrenzten Raum mindestens eine Rezirkulationsstruktur angeordnet ist, und wobei die oder jede Rezirkulationsstruktur auf die Seite höheren Drucks hin ausgerichtet ist.This problem is solved in that the sealing arrangement mentioned at the outset is developed by the features of the characterizing part of patent claim 1. According to the invention, the sealing projections are inclined or inclined in the axial direction towards a side of higher pressure, at least one recirculation structure being arranged in a space delimited by the at least two sealing projections and the corresponding inlet linings, and the or each recirculation structure being on the side of higher pressure is aligned.
Nach einer vorteilhaften Weiterbildung der Erfindung sind die Dichtungsvorsprünge als Dichtfins und die Einlaufbeläge als Wabenstrukturen ausgebildet.According to an advantageous development of the invention, the sealing projections are designed as sealing fins and the inlet linings as honeycomb structures.
Vorzugsweise weisen die mit einem Leitschaufelkranz zusammenwirkenden Dichtungsvorsprünge und die entsprechenden Einlaufbeläge des Leitschaufelkranzes unterschiedliche Radien auf, wobei Außenradien der Dichtungsvorsprünge sowie Innenradien der Einlaufbeläge in Richtung auf die Seite höheren Drucks hin zunehmen bzw. größer werden.The sealing projections interacting with a guide vane ring and the corresponding inlet linings of the guide vane ring preferably have different radii, with outer radii of the sealing projections and inner radii of the inlet linings increasing or increasing in the direction of the side of higher pressure.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den abhängigen Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. In der Zeichnung zeigt:Preferred developments of the invention result from the dependent subclaims and the following description. Exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being restricted to this. The drawing shows:
Fig. 1 : einen Teillängsschnitt durch einen Verdichter in Axialbauweise im Bereich eines Leitschaufelkranzes zur Verdeutlichung der erfindungsgemäßen Dichtungsanordnung.1: a partial longitudinal section through a compressor in axial design in the region of a guide vane ring to illustrate the sealing arrangement according to the invention.
Nachfolgend wird die hier vorliegende Erfindung unter Bezugnahme auf Fig. 1 in größerem Detail beschrieben.The present invention is described in greater detail below with reference to FIG. 1.
Fig. 1 zeigt einen schematisierten Querschnitt durch einen Verdichter 10 einer Gasturbine mit einem feststehenden Gehäuse 1 1 und einem gegenüber dem feststehenden Gehäuse 1 1 rotierenden Rotor 12, wobei das feststehende Gehäuse 1 1 sowie der Rotor 12 einen Hauptströmungskanal 13 begrenzen. Die Durchströmungsrichtung des Hauptströmungskanals 13 ist in Fig. 1 durch einen Pfeil 14 visualisiert.Fig. 1 shows a schematic cross section through a compressor 10 of a gas turbine with a fixed housing 11 and a rotor 12 rotating relative to the fixed housing 11, the fixed housing 11 and the rotor 12 delimiting a main flow channel 13. The direction of flow through the main flow channel 13 is visualized in FIG. 1 by an arrow 14.
Im Hauptströmungskanal 13 sind in axialer Richtung bzw. in Durchströmungsrichtung hintereinander mehrere feststehende Leitschaufelkränze 15 angeordnet, wobei Fig. 1 lediglich einen derartigen Leitschaufelkranz 15 zeigt. Jeder Leitschaufelkranz 15 wird durch mehrere Leitschaufeln 16 gebildet, die an einer axialen Position des Verdichters 10 in Umfangsrichtung desselben um den Rotor 12 herum angeordnet sind. Die feststehenden Leitschaufeln 16 sind mit einem radial außenliegenden Ende 17 in das Gehäuse 1 1 integriert. Zwischen einem dem radial außenliegenden Ende 17 gegenüberliegenden, radial innenliegenden Ende 18 der Leitschaufeln 16 und dem Rotor 12 ist ein Spalt 19 ausgebildet.A plurality of stationary guide vane rings 15 are arranged one behind the other in the main flow channel 13 in the axial direction or in the flow direction, FIG. 1 only showing such a guide vane ring 15. Each guide vane ring 15 is formed by a plurality of guide vanes 16 which are arranged around the rotor 12 at an axial position of the compressor 10 in the circumferential direction thereof. The fixed guide vanes 16 are integrated into the housing 11 with a radially outer end 17. A gap 19 is formed between a radially inner end 18 of the guide vanes 16 opposite the radially outer end 17 and the rotor 12.
Zwischen zwei benachbarten, feststehenden Leitschaufelkränzen 15 ist jeweils ein Laufschaufelkranz angeordnet. Fig. 1 zeigt einen derartigen Laufschaufelkranz 20, der aus mehreren Laufschaufeln 21 gebildet ist, die mit einem radial innenliegenden Ende 22 am Rotor 12 befestigt sind. Zwischen einem radial außenliegenden Ende 23 der Laufschaufeln 21 und dem Gehäuse 1 1 des Verdichters 10 ist wiederum ein Spalt ausgebildet. Zur Abdichtung dieses radialen Spalts zwischen den radial außenliegenden Enden 23 der rotierenden Laufschaufeln 20 und dem feststehenden Ge- häuse 1 1 ist dem Gehäuse 1 1 ein sogenannter Einlaufbelag 24 zugeordnet, der ein verschleißarmes Anstreifen der radial außenliegenden Enden 23 der Laufschaufeln 21 in das Gehäuse 1 1 des Verdichters 10 ermöglicht.A rotor blade ring is arranged between two adjacent, stationary guide vane rings 15. 1 shows such a rotor blade ring 20, which is formed from a plurality of rotor blades 21 which are fastened to the rotor 12 with a radially inner end 22. Again, a gap is formed between a radially outer end 23 of the blades 21 and the housing 11 of the compressor 10. To seal this radial gap between the radially outer ends 23 of the rotating blades 20 and the fixed gear Housing 1 1 is assigned to housing 1 1, a so-called run-in coating 24, which enables the radially outer ends 23 of rotor blades 21 to be rubbed against housing 1 1 of compressor 10 with little wear.
Die hier vorliegende Erfindung betrifft eine Dichtungsanordnung zur Abdichtung des Spalts 19 zwischen den radial innenliegenden Enden 18 der feststehenden Leitschaufeln 16 eines Leitschaufelkranzes 15 und dem Rotor 12 des Verdichters 10. Im gezeigten, bevorzugten Ausführungsbeispiel gemäß Fig. 1 umfasst diese Dichtungsanordnung zwei dem Rotor 12 zugeordnete Dichtungsvorsprünge 25 und 26. Es können auch mehr als zwei Dichtungsvorsprünge vorhanden sein. Die Dichtungsvorsprünge 25 und 26 sind als sogenannte Dichtfins ausgebildet und in axialer Richtung des Verdichters 10 voneinander beabstandet. Die Dichtungsvorsprünge 25 und 26 erstrecken sich über den gesamten Umfang des Rotors 12, sind also in Umfangsrichtung geschlossen. Die Dichtungsvorsprünge 25 und 26 wirken mit Einlaufbelägen 27 und 28 zusammen. Die Einlaufbeläge 27 und 28 sind den radial innenliegenden Enden 18 der feststehenden Leitschaufeln 16 zugeordnet, nämlich in die als Plattform ausgebildeten, radial innenliegenden Enden 18 der Leitschaufeln 16 integriert. Die Einlaufbeläge 27 und 28 sind demnach feststehend ausgebildet und die Dichtungsvorsprünge 25 und 26 rotieren zusammen mit dem Rotor 12 gegenüber den feststehenden Einlaufbelägen 27 und 28. Die Einlaufbeläge 27 und 28 sind vorzugsweise als Wabendichtungen ausgeführt, wobei Waben dieser Wabenstrukturen in Richtung auf die Dichtungsvorsprünge 25 und 26 offen ausgeführt sind.The present invention relates to a sealing arrangement for sealing the gap 19 between the radially inner ends 18 of the stationary guide vanes 16 of a guide vane ring 15 and the rotor 12 of the compressor 10. In the preferred exemplary embodiment shown in FIG. 1, this sealing arrangement comprises two associated with the rotor 12 Sealing protrusions 25 and 26. There may also be more than two sealing protrusions. The sealing projections 25 and 26 are designed as so-called sealing fins and are spaced apart from one another in the axial direction of the compressor 10. The sealing projections 25 and 26 extend over the entire circumference of the rotor 12, that is to say they are closed in the circumferential direction. The sealing projections 25 and 26 cooperate with inlet linings 27 and 28. The inlet linings 27 and 28 are assigned to the radially inner ends 18 of the fixed guide vanes 16, namely integrated into the radially inner ends 18 of the guide vanes 16 designed as a platform. The inlet linings 27 and 28 are accordingly designed to be stationary and the sealing projections 25 and 26 rotate together with the rotor 12 relative to the stationary inlet linings 27 and 28. The inlet linings 27 and 28 are preferably designed as honeycomb seals, with honeycombs of these honeycomb structures in the direction of the sealing projections 25 and 26 are open.
Bei dem in Fig. 1 dargestellten Verdichter 10 einer Gasturbine nimmt in Durchströmungsrichtung (Pfeil 14) der Gasdruck innerhalb des Verdichters zu. Im Sinne der hier vorliegenden Erfindung sind die Dichtungsvorsprünge 25 und 26, die - wie bereits erwähnt - als Dichtfins ausgebildet sind, in axialer Richtung zu einer Seite höheren Gasdrucks hin geneigt bzw. schräggestellt. Dies kann Fig. 1 entnommen werden. So zeigt Fig. 1, dass die Durchströmungsrichtung des Hauptströmungskanals 13 des Verdichters 10 von links nach rechts verläuft, also ein Gasdruck auf der rechten Seite der Leitschaufeln 16 höher ist als auf der linken Seite derselben. Die Dichtungsvorsprünge 25 und 26 sind mit ihren Spitzen zur rechten Seite hin, also zu der Seite höheren Gasdrucks hin, geneigt. Hierdurch wird die Dichtwirkung der Dichtungsvorsprünge 25 und 26 optimiert.In the compressor 10 of a gas turbine shown in FIG. 1, the gas pressure inside the compressor increases in the direction of flow (arrow 14). In the sense of the present invention, the sealing projections 25 and 26, which - as already mentioned - are designed as sealing fins, are inclined or inclined in the axial direction towards a side of higher gas pressure. This can be seen in FIG. 1. 1 shows that the flow direction of the main flow channel 13 of the compressor 10 runs from left to right, that is to say a gas pressure on the right side of the guide vanes 16 is higher than on the left side of the latter. The sealing projections 25 and 26 are with their tips to the right side, that is to the side higher gas pressure, inclined. This optimizes the sealing effect of the sealing projections 25 and 26.
Weiterhin ist erfindungsgemäß in einem von den Dichtungsvorsprüngen 25 und 26 sowie den korrespondierenden Einlaufbelägen 27 und 28 begrenzten Raum 29 eine Rezirkulationsstruktur 30 angeordnet. Die Rezirkulationsstruktur 30 ist dabei in das radial innenliegende Ende 18 der Leitschaufeln 16 des Leitschaufelkranzes 15 integriert, wobei die radial innenliegenden Enden 18 als Plattform der Leitschaufeln 16 ausgeführt sind. Die Einlaufbeläge 27 und 28, die ebenfalls dem radial innenliegenden Ende 18 der Leitschaufeln 16 zugeordnet sind, sind gemäß Fig. 1 zu beiden Seiten der Rezirkulationsstruktur 30 angeordnet. Es liegt im Sinne der hier vorliegenden Erfindung, dass die Rezirkulationsstruktur 30 ebenso wie die Dichtungsvorsprünge 25 und 26 auf die Seite höheren Gasdrucks hin ausgerichtet ist. Durch die Integration einer derart ausgebildeten Rezirkulationsstruktur 30 in die Dichtungsanordnung aus Dichtungsvorsprüngen 25 und 26 sowie korrespondierenden Einlaufbelägen 27 und 28 wird die Dichtwirkung nochmals optimiert.Furthermore, according to the invention, a recirculation structure 30 is arranged in a space 29 delimited by the sealing projections 25 and 26 and the corresponding inlet linings 27 and 28. The recirculation structure 30 is integrated into the radially inner end 18 of the guide vanes 16 of the guide vane ring 15, the radially inner ends 18 being designed as a platform for the guide vanes 16. The inlet linings 27 and 28, which are also assigned to the radially inner end 18 of the guide vanes 16, are arranged on both sides of the recirculation structure 30 according to FIG. 1. It is within the meaning of the present invention that the recirculation structure 30, like the sealing projections 25 and 26, is oriented towards the side of higher gas pressure. The sealing effect is further optimized by integrating a recirculation structure 30 designed in this way into the sealing arrangement comprising sealing projections 25 and 26 and corresponding inlet linings 27 and 28.
Wie Fig. 1 entnommen werden kann, verfügen die beiden Dichtungsvorsprünge 25 und 26 sowie die beiden mit den Dichtungsvorsprüngen 25 und 26 zusammenwirkenden Einlaufbeläge 27 und 28 über abgestufte Radien. Der in Strömungsrichtung (Pfeil 14) stromabwärts liegende Dichtungsvorsprung 26, der bei einem Verdichter demnach auf der Seite höheren Gasdrucks angeordnet ist wie der stromaufwärts liegende Dichtungsvorsprung 25, verfügt über einen gegenüber dem stromaufwärts liegenden Dichtungsvorsprung 25 vergrößerten Außenradius. Demzufolge verfügt auch der mit dem stromabwärts liegenden Dichtungsvorsprung 26 zusammenwirkende Einlaufbelag 28 über einen größeren Innendurchmesser als der mit dem stromaufwärts liegenden Dichtungsvorsprung 25 zusammenwirkende Einlaufbelag 27. Die Rezirkulationsstruktur 30 ragt über den stromabwärts angeordneten Einlaufbelag 28 radial hervor.As can be seen in FIG. 1, the two sealing projections 25 and 26 and the two inlet linings 27 and 28 interacting with the sealing projections 25 and 26 have stepped radii. The sealing protrusion 26 located downstream in the direction of flow (arrow 14), which in the case of a compressor is accordingly arranged on the side of higher gas pressure than the upstream sealing protrusion 25, has an outer radius that is larger than that of the upstream sealing protrusion 25. Accordingly, the inlet lining 28 cooperating with the downstream sealing projection 26 also has a larger inner diameter than the inlet lining 27 interacting with the upstream sealing projection 25. The recirculation structure 30 projects radially beyond the downstream inlet lining 28.
Obwohl, wie bereits erwähnt, in der schematisierten Darstellung gemäß Fig. 1 lediglich ein Leitschaufelkranz 15 gezeigt ist, sind in dem Verdichter 10 in axialer Richtung mehrere derartige Leitschaufelkränze hintereinander positioniert. Im Bereich jedes Leitschaufelkranzes kann dabei eine wie oben beschriebene Dichtungsanordnung zur Abdichtung des radialen Spalts 19 zwischen den radial innenliegenden Enden 18 der feststehenden Leitschaufeln und dem Rotor 12 angeordnet sein.Although, as already mentioned, only one guide vane ring 15 is shown in the schematic representation according to FIG. 1, a plurality of such guide vane rings are positioned one behind the other in the compressor 10 in the axial direction. In the area Each guide vane ring can have a sealing arrangement as described above for sealing the radial gap 19 between the radially inner ends 18 of the fixed guide vanes and the rotor 12.
Die hier vorliegende Erfindung findet bevorzugt Verwendung zur Reduzierung der Leckage in den sogenannten Statorwell-Cavities von Hochdruckverdichtern eines Flugtriebwerks. Obwohl die Verwendung bei Hochdruckverdichtern in Flugtriebwerken bevorzugt ist, kann die erfindungsgemäße Dichtungsanordnung auch in den Turbinen von Flugtriebwerken oder auch in stationären Gasturbinen Verwendung finden. The present invention is preferably used to reduce the leakage in the so-called statorwell cavities of high-pressure compressors of an aircraft engine. Although the use in high-pressure compressors in aircraft engines is preferred, the sealing arrangement according to the invention can also be used in the turbines of aircraft engines or in stationary gas turbines.

Claims

Patentansprüche claims
1. Dichtungsanordnung für eine Gasturbine, insbesondere für einen Verdichter eines Flugtriebwerks, zur Abdichtung eines Spalts (19) zwischen radial innenliegenden Enden (18) von Leitschaufeln (16) eines Leitschaufelkranzes (15) und einem Rotor (12), wobei der Rotor (12) mindestens zwei in Umfangsrichtung des Rotors (12) verlaufende, mit axialem Abstand zueinander positionierte Dichtungsvorsprünge (25, 26) aufweist, die in Kombination mit den radial innenliegenden Enden (18) der Leitschaufeln (16) zugeordneten Einlaufbelägen (27, 28) eine Abdichtung des Spalts (19) bewirken, dadurch gekennzeichnet, dass: a) die Dichtungsvorsprünge (25, 26) in axialer Richtung zu einer Seite höheren Drucks hin geneigt bzw. schräggestellt sind, b) in einem von den mindestens zwei Dichtungsvorsprüngen (25, 26) und den entsprechenden Einlaufbelägen (27, 28) begrenzten Raum (29) mindestens eine Rezirkulationsstruktur (30) angeordnet ist, wobei die oder jede Rezirkulationsstruktur (30) auf die Seite höheren Drucks hin ausgerichtet ist.1. Sealing arrangement for a gas turbine, in particular for a compressor of an aircraft engine, for sealing a gap (19) between radially inner ends (18) of guide vanes (16) of a guide vane ring (15) and a rotor (12), the rotor (12 ) has at least two sealing projections (25, 26) which run in the circumferential direction of the rotor (12) and are at an axial distance from one another and which, in combination with the radially inner ends (18) of the guide vanes (16), have a seal (27, 28) of the gap (19), characterized in that: a) the sealing projections (25, 26) are inclined or inclined in the axial direction towards a side of higher pressure, b) in one of the at least two sealing projections (25, 26) and the corresponding inlet coverings (27, 28) delimiting space (29) at least one recirculation structure (30) is arranged, the or each recirculation structure (30) on the side higher pressure is aligned.
2. Dichtungsanordnung nach Anspruch 1, dadurch gekennzeichnet, dass die oder jede Rezirkulationsstruktur (30) in eine radial innenliegende Plattform der Leitschaufeln (16) des Leitschaufelkranzes (15) integriert ist.2. Sealing arrangement according to claim 1, characterized in that the or each recirculation structure (30) in a radially inner platform of the guide vanes (16) of the guide vane ring (15) is integrated.
3. Dichtungsanordnung nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Dichtungsvorsprünge (25, 26) als Dichtfins ausgebildet sind.3. Sealing arrangement according to claim 1 or 2, characterized in that the sealing projections (25, 26) are designed as sealing fins.
4. Dichtungsanordnung nach einem oder mehreren der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Einlaufbeläge (27, 28) als Wabenstrukturen ausgebildet sind.4. Sealing arrangement according to one or more of claims 1 to 3, characterized in that the inlet linings (27, 28) are designed as honeycomb structures.
5. Dichtungsanordnung nach Anspruch 4, dadurch gekennzeichnet, dass Waben der Wabenstrukturen in Richtung auf die Dichtungsvorsprünge (25, 26) offen ausgebildet sind. 5. Sealing arrangement according to claim 4, characterized in that honeycombs of the honeycomb structures in the direction of the sealing projections (25, 26) are open.
6. Dichtungsanordnung nach einem oder mehreren der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die mit einem Leitschaufelkranz zusammenwirkenden Dichtungsvorsprünge (25, 26) und die entsprechenden Einlaufbeläge (27, 28) des Leitschaufelkranzes (15) unterschiedliche Radien aufweisen, wobei Außenradien der Dichtungsvorsprünge (25, 26) sowie Innenradien der Einlaufbeläge (27, 28) in Richtung auf die Seite höheren Drucks hin zunehmen bzw. größer werden.6. Sealing arrangement according to one or more of claims 1 to 5, characterized in that the sealing projections (25, 26) interacting with a guide vane ring and the corresponding inlet linings (27, 28) of the guide vane ring (15) have different radii, the outer radii of the sealing projections (25, 26) and the inner radii of the inlet linings (27, 28) increase or become larger in the direction of the higher pressure side.
7. Dichtungsanordnung nach einem oder mehreren der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die innerhalb eines Hauptströmungskanals (13) angeordneten Leitschaufeln (16) in axialer Richtung des Hauptströmungskanals (13) hintereinander angeordnete Leitschaufelkränze (15) bilden, wobei zwischen jeweils zwei benachbarten Leitschaufelkränzen (15) jeweils ein Laufschaufelkranz (20) angeordnet ist, und wobei im Bereich jedes Leitschaufelkranzes (15) ein Spalt (19) zwischen den Leitschaufeln (16) und einem Rotor (12) durch mindestens zwei in Umfangsrichtung des Rotors (12) verlaufende, mit axialem Abstand zueinander positionierte Dichtungsvorsprünge (25, 26), die mit den radial innenliegenden Enden (18) der Leitschaufeln (16) zugeordneten Einlaufbelägen (27, 28) zusammenwirken, abgedichtet ist.7. Sealing arrangement according to one or more of claims 1 to 6, characterized in that the guide vanes (16) arranged within a main flow channel (13) form successively arranged guide vane rings (15) in the axial direction of the main flow channel (13), with two adjacent ones in each case Guide vane rings (15) each have a rotor vane ring (20), and in the region of each guide vane ring (15) there is a gap (19) between the guide vanes (16) and a rotor (12) through at least two running in the circumferential direction of the rotor (12) , sealing projections (25, 26) positioned at an axial distance from one another, which cooperate with the radially inner ends (18) of the guide vanes (16) associated with the inlet linings (27, 28).
8. Dichtungsanordnung nach Anspruch 7, dadurch gekennzeichnet, dass im Bereich jedes Leitschaufelkranzes (15) die Dichtungsvorsprünge (25, 26) in axialer Richtung zu einer Seite höheren Drucks hin geneigt bzw. schräggestellt sind.8. Sealing arrangement according to claim 7, characterized in that in the region of each guide vane ring (15) the sealing projections (25, 26) are inclined or inclined in the axial direction towards a side of higher pressure.
9. Dichtungsanordnung nach Anspruch 7 oder 8, dadurch gekennzeichnet, dass im Bereich jedes Leitschaufelkranzes (15) in den von den mindestens zwei Dichtungsvorsprüngen (25, 26) und den entsprechenden Einlaufbelägen (27, 28) begrenzten Raum (29) mindestens eine Rezirkulationsstruktur (30) angeordnet ist, wobei die oder jede Rezirkulationsstruktur (30) auf die Seite höheren Drucks hin ausgerichtet ist. 9. Sealing arrangement according to claim 7 or 8, characterized in that in the region of each guide vane ring (15) in the space delimited by the at least two sealing projections (25, 26) and the corresponding inlet linings (27, 28) (29) at least one recirculation structure ( 30) is arranged, wherein the or each recirculation structure (30) is oriented towards the higher pressure side.
10. Turboverdichter in Axialbauweise und/oder Diagonalbauweise und/oder Radialbauweise, mit einer Dichtungsanordnung nach einem oder mehreren der Ansprüche 1 bis 9.10. turbocompressor in axial construction and / or diagonal construction and / or radial construction, with a sealing arrangement according to one or more of claims 1 to 9.
1 1. Flugtriebwerk, mit einem Turboverdichter nach Anspruch 10.1 1. aircraft engine, with a turbocompressor according to claim 10.
12. Stationäre Gasturbine, mit einem Turboverdichter nach Anspruch 10. 12. Stationary gas turbine, with a turbocompressor according to claim 10.
EP04786886A 2003-10-17 2004-09-30 Sealing arrangement for a gas turbine Expired - Fee Related EP1673519B1 (en)

Applications Claiming Priority (2)

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DE2003148290 DE10348290A1 (en) 2003-10-17 2003-10-17 Sealing arrangement for a gas turbine
PCT/DE2004/002174 WO2005040561A1 (en) 2003-10-17 2004-09-30 Sealing arrangement for a gas turbine

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EP1673519A1 true EP1673519A1 (en) 2006-06-28
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EP1673519B1 (en) 2012-08-29
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US20070274825A1 (en) 2007-11-29
US9011083B2 (en) 2015-04-21

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