EP2818643A1 - Sealing device and turbo-machine - Google Patents

Sealing device and turbo-machine Download PDF

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Publication number
EP2818643A1
EP2818643A1 EP14172050.8A EP14172050A EP2818643A1 EP 2818643 A1 EP2818643 A1 EP 2818643A1 EP 14172050 A EP14172050 A EP 14172050A EP 2818643 A1 EP2818643 A1 EP 2818643A1
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EP
European Patent Office
Prior art keywords
sealing
ring
wall
sealing device
annular
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Granted
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EP14172050.8A
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German (de)
French (fr)
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EP2818643B1 (en
Inventor
Manfred Feldmann
Thomas Hess
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP2818643A1 publication Critical patent/EP2818643A1/en
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    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material

Definitions

  • the invention relates to a sealing device for a turbomachine according to the preamble of patent claim 1, as for example from the WO 2009/118490 A2 is known, and a turbomachine.
  • the two stator rings conventionally have very different temperatures, so that the fish mouth seals must be designed such that resulting thermal strains are kept or reduced to an acceptable level of stress.
  • the two following constructions for forming the fishmouth seals are known:
  • the inner stator ring is formed integrally with the outer stator ring of the vane ring.
  • this construction often leads to crack formation in the hot transition region between the stator rings.
  • the inner stator ring is bolted to a forward radial flange of the vane ring.
  • the second construction shows a better behavior with respect to the thermally induced stresses in the fish mouth seal, it creates a potentially large leakage area by the arrangement of the inner stator ring on the vane ring.
  • the object of the invention is to provide a sealing device for sealing a radially inner gas channel between a vane ring and a rotor of a turbomachine such as a gas turbine, which eliminates the aforementioned disadvantages and allows a radial thermal expansion compensation.
  • a turbomachine with an improved seal of an inner gas channel between a vane ring and a rotor.
  • the sealing device has an outer radial flange for connection to the integral inner ring of the vane ring and a double-walled cylinder with an oriented in a first direction outer wall and with an oriented in an opposite direction inner wall, which are interconnected via an annular arc, wherein the radial flange in the outer wall goes over and the cylinder forms the sealing ring.
  • the inner wall passes over an annular web in at least one parallel to the first direction or to the opposite direction oriented inner body portion for radially inner receiving a sealing structure, wherein the sealing device via their individual, integrally formed sections a uniform, preferably relatively small, wall thickness has, so that the sealing device is resilient within certain limits, in particular, the annular arc and the annular web act as radial spring elements.
  • the sealing device can be cohesively, for example by means of soldering, or non-positively and / or positively be connected to the vane ring.
  • the frictional connection or positive force fit is such that leakage flows in the connection region between the guide vane ring and the radial flange of the sealing device are prevented.
  • the inner wall passes via an annular web in at least one parallel to the first direction or the opposite direction oriented inner body portion for radially inner receiving a sealing structure.
  • the double-walled cylinder and the at least one inner body portion form a kind of three-walled cylinder.
  • the annular web is preferably relatively thin-walled.
  • the sealing ring forms a bearing element of the cylinder.
  • outer wall may extend downstream and the inner wall upstream, wherein the sealing ring is an integral portion of the outer wall.
  • the sealing device may have only one downstream body portion for receiving a sealing structure.
  • the inner wall forms the sealing ring.
  • the outer wall may for this purpose be directed upstream, whereas the inner wall is directed downstream.
  • the sealing ring is not a supporting structure of the cylinder, so that the sealing ring can have an optimally adapted to its actual sealing task geometry.
  • the sealing means may also include an upstream inner body portion and a downstream inner body portion for receiving a sealing structure. Characterized in that extends from the annular land a body portion downstream and a body portion upstream, it is loaded by the body portions substantially symmetrically or evenly.
  • the sealing device can be optimally adapted to the respective rotor and stator geometry if it is produced generatively.
  • the production costs and / or the production costs are / are reduced by the generative production, since a joining of a plurality of individual parts is eliminated.
  • the sealing structure may be integrally formed with the body portions so that it may also have an optimum shape and material structure and, moreover, need not be fixed to the sealing means in a separate assembly step.
  • a preferred turbomachine has at least one sealing device according to the invention for sealing a radially inner gas channel.
  • the sealing device can be cohesively, for example by means of soldering or non-positively and / or positively, for example by means of a screw, be connected to the inner ring of a vane ring. Due to the radial thermal expansion compensation, the inner gas channel is better sealed compared to known sealing devices for hot gas flow.
  • FIG. 1 shows a first embodiment of a sealing device 1 according to the invention for sealing a radially inner gas channel 2 between a vane ring 4 and a rotor 6 of a turbomachine such as a gas turbine and in particular an aircraft engine shown.
  • the sealing device 1 has a sealing ring 8 for forming a sealing space 10 with a rear portion of an integral inner ring 12 of the vane ring 4.
  • the sealing device 1 has for connection to the inner ring 12 an outwardly oriented radial flange 18 and the inner ring 12 has to receive the sealing device 1 an inwardly directed annular flange 20.
  • the sealing device 1 by means of a plurality of holes 22 through the radial flange 18 and the annular flange 20 guided fasteners 24 connected as screw-nut systems.
  • the radial flange 18 is pressed so strong against the annular flange 20 that no leakage current can form between them.
  • the sealing device 1 can be bonded to the inner ring 12 by material bonding, for example by means of soldering.
  • an abutment region between the radial flange 18 and the annular flange 20 is provided at an angle with an axial abutment boundary 25 and a radial abutment boundary 27.
  • the sealing device 1 has a double-walled cylinder 26, which runs approximately coaxially with the axial direction of the turbomachine in the mounted state.
  • the cylinder 26 has an outer wall 28 and an inner wall 30, which are connected to each other via an annular arc 32.
  • the cylinder 26 thus has a U-shaped or hairpin-like cross section, whereby different radial thermal expansions of the vane ring 4 to the sealing ring 8 can be compensated without excessive tension.
  • the sealing ring 8 is formed as an integral portion of the outer wall 28. Due to the Koaxiltician of the cylinder 26 of the sealing ring 8 forming portion or the sealing ring 8 extends approximately parallel to the rear portion of the inner ring 12th
  • the outer wall 28 forming the sealing ring 8 extends starting from the radial flange 18 in a first direction, as shown in FIG FIG. 1 downstream, and the inner wall 30 extends in an opposite direction, as shown in FIG FIG. 1 upstream of the main stream.
  • the inner wall 30 is arranged radially inward to the outer wall 28 and has a radially outwardly offset wall portion 34 which extends approximately to the radial height of the outer wall 28.
  • the wall portion 34 goes into a radially inwardly annular ridge 36 via, which merges into a downstream inner body portion 38.
  • the sealing device 1 has an approximately S-shaped cross-section.
  • the inner body portion 38 is disposed radially inward of the inner wall 30 and terminates short of an axial position of the annular arc 32. In the embodiment shown, it is designed stepwise and provided in its one rotor drum 39 side facing with a sealing structure or inlet structure 40.
  • the sealing structure 40 acts in combination with rotor-side sealing fins 42 as a labyrinth seal, by means of which a flow around the vane ring 4 in the region of its rotor drum 29 facing blade ends is prevented.
  • the sealing device 1 via its individual integral sections - radial flange 18, cylinder 26 with sealing ring 8, ring land 36 and inner body portion 38 - preferably a uniform wall thickness.
  • the wall thickness is relatively low, whereby the sealing means 1 is not rigid, but also has resilient or elastic properties.
  • the ring bottom 32 and the annular web 36 act as radial spring elements.
  • the radial flange 18 is located approximately centrally between an axial position of the annular web 36 and the axial position of the annular arc 32.
  • the sealing device 1 is produced generatively, for example by means of a laser sintering process or a selective laser melting process.
  • the sealing device 1 is thus preferably produced as a single part in a single process.
  • FIG. 2 a second embodiment of the sealing device 1 of a flow machine according to the invention is shown.
  • This exemplary embodiment likewise has a sealing ring 8, a radial flange 18, a double-walled cylinder 26 running coaxially in the mounted state relative to the axial direction of the turbomachine, an annular web 36 and a sealing structure 40.
  • the sealing ring 8 is not formed in this embodiment as an integral portion of the outer wall 28, but as an integral portion which extends from a free end of the inner wall 30 to the front.
  • the sealing ring 8 is provided in a stepped manner with a free peripheral edge 46 lying radially outwards relative to the inner wall 30 to a radial height of the outer wall 28.
  • the sealing ring 8 extends with its outwardly offset and the peripheral edge 46 forming annular portion 48 approximately parallel to the rear portion of the inner ring 12 of the vane ring 4th
  • the sealing device 1 in addition to an inner body portion 38 extending upstream from an annular ridge 36, an upstream extending inner body portion 50, which are provided together with a continuous sealing structure 40.
  • the sealing device 1 after FIG. 2 preferably a uniform relatively small wall thickness over its individual integral sections - radial flange 18, cylinder 26 with sealing ring 8, annular web 36 and inner body sections 38, 50 - and is thus resilient under certain limits.
  • the ring bottom 32 and the annular web 36 act as radial spring elements.
  • the radial flange 18 is located approximately centrally between an axial position of the annular arc 32 and an axial position of the free peripheral edge 46 of the sealing ring 8.
  • a front Fischmauldichtung and thus a hub-side sealing space between an upstream or front blade row and the vane ring 4 are formed.
  • the front sealing space between the inner wall portion 34 and the outer inner ring 12 may be formed, in which case the front guide blade row is immersed with a rear platform ring overhang in this front sealing space.
  • a sealing device for sealing a radially inner gas channel between a vane ring and a rotor of a turbomachine, the sealing device having a sealing ring for forming a sealing space with a directed towards a main flow rear portion of an integral inner ring of the vane ring into which a front platform overhang ring a immersed downstream row of blades, and wherein the sealing means has an outer radial flange for connection to the integral inner ring of the vane ring and a double-walled cylinder having a oriented in a first direction outer wall and with an oriented in an opposite direction inner wall, which are interconnected via a ring arc the radial flange merges into the outer wall of the cylinder and the cylinder forms the sealing ring, as well as a turbomachine.

Abstract

Offenbart ist eine Dichteinrichtung (1) zum Abdichten eines radial inneren Gaskanals (2) zwischen einem Leitschaufelkranz (4) und einem Rotor (6) einer Strömungsmaschine, wobei die Dichteinrichtung (1) einen Dichtring (8) zum Bilden eines Dichtraums (10) mit einem in Richtung einer Hauptströmung betrachtet hinteren Abschnitt eines integralen Innenrings (12) des Leitschaufelkranzes (4) hat, in den ein vorderer Plattformüberhangring (14) einer stromabwärtigen Laufschaufelreihe eintaucht, und wobei die Dichteinrichtung (1) einen äußeren Radialflansch (18) zur Anbindung an den integralen Innenring (12) und einen doppelwandigen Zylinder (26) mit einer in eine erste Richtung orientierten Außenwandung (28) und mit einer in eine Gegenrichtung orientierten Innenwandung (30) hat, die über einen Ringbogen (32) miteinander verbunden sind, wobei der Radialflansch (18) in die Außenwandung (28) übergeht und der Zylinder (26) den Dichtring bildet (8), wobei die Innenwandung (30) über einen Ringsteg (36) in wenigstens einen parallel zur ersten Richtung bzw. zur Gegenrichtung orientierten inneren Körperabschnitt (38,50) zur radial inneren Aufnahme einer Dichtstruktur (40) übergeht, wobei die Dichteinrichtung (1) über ihre einzelnen, integral miteinander ausgebildeten Abschnitte eine einheitliche, vorzugsweise verhältnismäßig geringe, Wandstärke aufweist, so dass die Dichteinrichtung (1) in gewissen Grenzen federelastisch ist, wobei insbesondere der Ringbogen (32) und der Ringsteg (36) als radiale Federelemente wirken, sowie eine Strömungsmaschine.Disclosed is a sealing device (1) for sealing a radially inner gas channel (2) between a vane ring (4) and a rotor (6) of a turbomachine, wherein the sealing device (1) has a sealing ring (8) for forming a sealing space (10) a rearward portion, viewed in the direction of a main flow, of an integral inner ring (12) of the vane ring (4) into which a front platform overhang ring (14) of a downstream blade row dips, and wherein the sealing device (1) has an outer radial flange (18) for connection to the integral inner ring (12) and a double - walled cylinder (26) having an outer wall (28) oriented in a first direction and an inner wall (30) oriented in an opposite direction and interconnected by an annular arc (32) Radial flange (18) merges into the outer wall (28) and the cylinder (26) forms the sealing ring (8), wherein the inner wall (30) via a Ring web (36) in at least one parallel to the first direction or to the opposite direction oriented inner body portion (38,50) for radially inner receiving a sealing structure (40) merges, wherein the sealing means (1) via their individual, integrally formed with each other sections a uniform , preferably relatively small, wall thickness, so that the sealing device (1) is resilient under certain limits, in particular, the annular arc (32) and the annular web (36) act as radial spring elements, and a turbomachine.

Description

Die Erfindung betrifft eine Dichteinrichtung für eine Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1, wie sie zum Beispiel aus der WO 2009/118490 A2 bekannt ist, und eine Strömungsmaschine.The invention relates to a sealing device for a turbomachine according to the preamble of patent claim 1, as for example from the WO 2009/118490 A2 is known, and a turbomachine.

Zur Abdichtung eines radial inneren Gaskanals zwischen einem Leitschaufelkranz und einem Rotor einer Strömungsmaschine wie eine Gasturbine und insbesondere ein Flugtriebwerk werden sogenannte Fischmauldichtungen verwendet, bei denen ein umlaufender im Wesentlichen zylindrischer Rotorring einer Laufschaufelreihe in einem ringförmigen Dichtraum läuft, der von einem radial inneren Statorring und einem radial äußeren Statorring des Leitschaufelkranzes begrenzt wird. Im Dichtraum bilden sich Wirbel aus, mittels denen ein Heißgaseinzug aus dem Heizgaskanal in den inneren Gaskanal verhindert werden soll.To seal a radially inner gas channel between a vane ring and a rotor of a turbomachine such as a gas turbine and in particular an aircraft engine so-called Fischmauldichtungen be used in which a circumferential substantially cylindrical rotor ring of a blade row runs in an annular sealing space of a radially inner stator and a radially outer stator ring of the vane ring is limited. In the sealing space vortex form, by means of which a hot gas inlet from the Heizgaskanal should be prevented in the inner gas channel.

Die beiden Statorringe haben herkömmlicherweise sehr unterschiedliche Temperaturen, so dass die Fischmauldichtungen derart gestaltet sein müssen, dass resultierende thermische Dehnungen in einem akzeptablen Spannungsniveau gehalten bzw. abgebaut werden.The two stator rings conventionally have very different temperatures, so that the fish mouth seals must be designed such that resulting thermal strains are kept or reduced to an acceptable level of stress.

Zusätzlich zur Abdichtung des inneren Gaskanals muss eine Umströmung des Leitschaufelkranzes zwischen der Leitschaufelreihe und einer Rotortrommel verhindert werden, was in der Regel durch eine Labyrinthdichtung innerhalb des inneren Gaskanals realisiert wird.In addition to sealing the inner gas channel, flow around the vane ring between the row of vanes and a rotor drum must be prevented, which is typically accomplished by a labyrinth seal within the inner gas channel.

Grundsätzlich sind die beiden folgenden Konstruktionen zur Ausbildung der Fischmauldichtungen bekannt: Bei einer ersten Konstruktion wird der innere Statorring integral mit dem äußeren Statorring des Leitschaufelkranzes ausgebildet. Diese Konstruktion führt jedoch durch die thermisch bedingten Spannungen nicht selten zu Rissbildung im heißen Übergangsbereich zwischen den Statorringen. Bei einer zweiten Konstruktion ist der innere Statorring an einem vorderen Radialflansch des Leitschaufelkranzes angeschraubt. Die zweite Konstruktion zeigt zwar ein besseres Verhalten bezüglich der thermisch induzierten Spannungen in die Fischmauldichtung, schafft jedoch durch die Anlage des inneren Statorrings am Leitschaufelkranz eine potentielle große Leckagefläche.Basically, the two following constructions for forming the fishmouth seals are known: In a first construction, the inner stator ring is formed integrally with the outer stator ring of the vane ring. However, due to the thermally induced stresses, this construction often leads to crack formation in the hot transition region between the stator rings. In a second construction, the inner stator ring is bolted to a forward radial flange of the vane ring. Although the second construction shows a better behavior with respect to the thermally induced stresses in the fish mouth seal, it creates a potentially large leakage area by the arrangement of the inner stator ring on the vane ring.

Aufgabe der Erfindung ist es, eine Dichteinrichtung zum Abdichten eines radial inneren Gaskanals zwischen einem Leitschaufelkranz und einem Rotor einer Strömungsmaschine wie eine Gasturbine zu schaffen, die die vorgenannten Nachteile beseitigt und einen radial thermischen Dehnungsausgleich ermöglicht. Zudem ist es Aufgabe der Erfindung, eine Strömungsmaschine mit einer verbesserten Abdichtung eines inneren Gaskanals zwischen einem Leitschaufelkranz und einem Rotor zu schaffen.The object of the invention is to provide a sealing device for sealing a radially inner gas channel between a vane ring and a rotor of a turbomachine such as a gas turbine, which eliminates the aforementioned disadvantages and allows a radial thermal expansion compensation. In addition, it is an object of the invention to provide a turbomachine with an improved seal of an inner gas channel between a vane ring and a rotor.

Diese Aufgabe wird gelöst durch eine Dichteinrichtung mit den Merkmalen des Patentanspruchs 1 und durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 8.This object is achieved by a sealing device having the features of patent claim 1 and by a turbomachine having the features of patent claim 8.

Eine erfindungsgemäße Dichteinrichtung zum Abdichten eines radial inneren Gaskanals zwischen einem Leitschaufelkranz und einem Rotor einer Strömungsmaschine hat einen Dichtring zum Bilden eines Dichtraums mit einem in Richtung einer Hauptströmung betrachtet hinteren Abschnitt eines integralen Innenrings des Leitschaufelkranzes, in den ein vorderer Plattformüberhangring einer stromabwärtigen Laufschaufelreihe eintaucht. Erfindungsgemäß hat die Dichteinrichtung einen äußeren Radialflansch zur Anbindung an den integralen Innenring des Leitschaufelkranzes und einen doppelwandigen Zylinder mit einer in eine erste Richtung orientierten Außenwandung und mit einer in eine Gegenrichtung orientierten Innenwandung, die über einen Ringbogen miteinander verbunden sind, wobei der Radialflansch in die Außenwandung übergeht und der Zylinder den Dichtring bildet. Darüber hinaus geht erfindungsgemäß die Innenwandung über einen Ringsteg in wenigstens einen parallel zur ersten Richtung bzw. zur Gegenrichtung orientierten inneren Körperabschnitt zur radial inneren Aufnahme einer Dichtstruktur übergeht, wobei die Dichteinrichtung über ihre einzelnen, integral miteinander ausgebildeten Abschnitte eine einheitliche, vorzugsweise verhältnismäßig geringe, Wandstärke aufweist, so dass die Dichteinrichtung in gewissen Grenzen federelastisch ist, wobei insbesondere der Ringbogen und der Ringsteg als radiale Federelemente wirken.A sealing device according to the invention for sealing a radially inner gas passage between a vane ring and a rotor of a turbomachine has a sealing ring for forming a sealing space with a mainstream downstream portion of an integral inner ring of the vane ring into which a front platform overhang ring of a downstream blade row is immersed. According to the invention, the sealing device has an outer radial flange for connection to the integral inner ring of the vane ring and a double-walled cylinder with an oriented in a first direction outer wall and with an oriented in an opposite direction inner wall, which are interconnected via an annular arc, wherein the radial flange in the outer wall goes over and the cylinder forms the sealing ring. In addition, according to the invention, the inner wall passes over an annular web in at least one parallel to the first direction or to the opposite direction oriented inner body portion for radially inner receiving a sealing structure, wherein the sealing device via their individual, integrally formed sections a uniform, preferably relatively small, wall thickness has, so that the sealing device is resilient within certain limits, in particular, the annular arc and the annular web act as radial spring elements.

Dadurch, dass der Radialflansch unmittelbar in den Zylinder übergeht, der Zylinder doppelwandig in U-Form bzw. in Form einer Haarnadel gestaltet ist und den Dichtring aufnimmt, ist der Dichtring schwimmend gelagert und radiale thermische Dehnungen des Leitschaufelkranzes werden ohne überhöhte Spannungen ausgeglichen. Die Dichteinrichtung kann stoffschlüssig, beispielsweise mittels Lötens, oder kraftschlüssig und/oder formschlüssig mit dem Leitschaufelkranz verbunden werden. Der Kraftschluss bzw. Kraftformschluss, beispielsweise mittels einer Verschraubung, ist derart, dass Leckageströme im Verbindungsbereich zwischen dem Leitschaufelkranz und dem Radialflansch der Dichteinrichtung unterbunden werden.Characterized in that the radial flange merges directly into the cylinder, the cylinder is double-walled in U-shape or in the form of a hairpin and receives the sealing ring, the sealing ring is floating and radial thermal expansions of the vane ring are compensated without excessive stresses. The sealing device can be cohesively, for example by means of soldering, or non-positively and / or positively be connected to the vane ring. The frictional connection or positive force fit, for example by means of a screw connection, is such that leakage flows in the connection region between the guide vane ring and the radial flange of the sealing device are prevented.

Um eine Umströmung des Leitschaufelkranzes zwischen dem Leitschaufelkranz und einer Rotortrommel zu verhindern, geht die Innenwandung über einen Ringsteg in wenigstens einen parallel zur ersten Richtung bzw. zur Gegenrichtung orientierten inneren Körperabschnitt zur radial inneren Aufnahme einer Dichtstruktur über. Somit bilden der doppelwandige Zylinder und der wenigstens eine innere Körperabschnitt eine Art dreifach-wandigen Zylinder.In order to prevent flow around the vane ring between the vane ring and a rotor drum, the inner wall passes via an annular web in at least one parallel to the first direction or the opposite direction oriented inner body portion for radially inner receiving a sealing structure. Thus, the double-walled cylinder and the at least one inner body portion form a kind of three-walled cylinder.

Um einen unverhältnismäßigen Wärmeeintrag über den Ringsteg in die Innennwandung zu vermeiden und um eine gewisse Elastizität der Körperabschnitte zu erhalten, ist der Ringsteg vorzugsweise verhältnismäßig dünnwandig.In order to avoid a disproportionate heat input via the annular web in the Innennwandung and to obtain a certain elasticity of the body portions, the annular web is preferably relatively thin-walled.

Bei einem kompakten Ausführungsbeispiel bildet der Dichtring ein tragendes Element des Zylinders. Hierzu kann sich Außenwandung stromabwärts und die Innenwandung stromaufwärts erstrecken, wobei der Dichtring ein integraler Abschnitt der Außenwandung ist. Die Dichteinrichtung kann zum Beispiel nur einen nach stromabwärts gerichteten inneren Körperabschnitt zur Aufnahme einer Dichtstruktur aufweisen.In a compact embodiment, the sealing ring forms a bearing element of the cylinder. For this purpose, outer wall may extend downstream and the inner wall upstream, wherein the sealing ring is an integral portion of the outer wall. For example, the sealing device may have only one downstream body portion for receiving a sealing structure.

Bei einem weiteren Ausführungsbeispiel bildet die Innenwandung den Dichtring. Die Außenwandung kann hierzu stromaufwärts gerichtet sein, wohingegen die Innenwandung stromabwärts gerichtet ist. Bei diesem Ausführungsbeispiel ist der Dichtring keine tragende Struktur des Zylinders, so dass der Dichtring eine an seine eigentliche Dichtaufgabe optimal angepasste Geometrie aufweisen kann. Die Dichteinrichtung kann auch einen stromaufwärts gerichteten inneren Körperabschnitt und in einen stromabwärts gerichteten inneren Körperabschnitt zur Aufnahme einer Dichtstruktur aufweisen. Dadurch, dass sich von dem Ringsteg ein Körperabschnitt stromabwärts und ein Körperabschnitt stromaufwärts erstreckt, wird dieser durch die Körperabschnitte im Wesentlichen symmetrisch bzw. gleichmäßig belastet. Um die auf den Radialflansch wirkenden Belastungen durch den Zylinder und/oder durch die Körperabschnitte gering zu halten bzw. auf die Dichteinrichtung wirkenden Belastungen nahezu gleichmäßig in den Radialflansch einzuleiten, ist es vorteilhaft, wenn der Radialflansch in Axialrichtung der Dichteinrichtung betrachtet etwa mittig derselben angeordnet ist.In a further embodiment, the inner wall forms the sealing ring. The outer wall may for this purpose be directed upstream, whereas the inner wall is directed downstream. In this embodiment, the sealing ring is not a supporting structure of the cylinder, so that the sealing ring can have an optimally adapted to its actual sealing task geometry. The sealing means may also include an upstream inner body portion and a downstream inner body portion for receiving a sealing structure. Characterized in that extends from the annular land a body portion downstream and a body portion upstream, it is loaded by the body portions substantially symmetrically or evenly. In order to keep the forces acting on the radial flange through the cylinder and / or through the body sections low or acting on the sealing device loads almost evenly introduced into the radial flange, it is advantageous if the radial flange in the axial direction of the sealing device viewed approximately centrally disposed the same.

Die Dichteinrichtung kann bzgl. ihrer Form und Materialstruktur optimal an die jeweilige Rotor- und Statorgeometrie angepasst werden, wenn sie generativ hergestellt ist. Zudem wird/werden durch die generative Herstellung der Fertigungsaufwand und die Herstellungskosten reduziert, da ein Fügen einer Vielzahl von Einzelteilen entfällt. Ferner kann durch die generative Herstellung die Dichtstruktur integral mit den Körperabschnitten ausgebildet werden, so dass sie ebenfalls eine optimale Form und Materialstruktur aufweisen kann und außerdem nicht in einem gesonderten Montageschritt an der Dichteinrichtung befestigt werden muss.With regard to its shape and material structure, the sealing device can be optimally adapted to the respective rotor and stator geometry if it is produced generatively. In addition, the production costs and / or the production costs are / are reduced by the generative production, since a joining of a plurality of individual parts is eliminated. Further, by the generative production, the sealing structure may be integrally formed with the body portions so that it may also have an optimum shape and material structure and, moreover, need not be fixed to the sealing means in a separate assembly step.

Eine bevorzugte Strömungsmaschine hat zumindest eine erfindungsgemäße Dichteinrichtung zum Abdichten eines radial inneren Gaskanals. Die Dichteinrichtung kann stoffschlüssig beispielweise mittels Verlötens oder kraftschlüssig und/oder formschlüssig, beispielsweise mittels einer Schraubverbindung, am Innenring eines Leitschaufelkranzes angebunden sein. Durch den radial thermischen Dehnungsausgleich wird der innere Gaskanal im Vergleich zu bekannten Dichteinrichtungen zum Heißgasstrom besser abgedichtet.A preferred turbomachine has at least one sealing device according to the invention for sealing a radially inner gas channel. The sealing device can be cohesively, for example by means of soldering or non-positively and / or positively, for example by means of a screw, be connected to the inner ring of a vane ring. Due to the radial thermal expansion compensation, the inner gas channel is better sealed compared to known sealing devices for hot gas flow.

Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.

Im Folgenden werden bevorzugte Ausführungsbeispiele der Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigen:

Figur 1
ein erstes Ausführungsbeispiel einer erfindungsgemäßen Dichteinrichtung, und
Figur 2
ein zweites Ausführungsbeispiel der erfindungsgemäßen Dichteinrichtung.
In the following preferred embodiments of the invention will be explained in more detail with reference to schematic representations. Show it:
FIG. 1
a first embodiment of a sealing device according to the invention, and
FIG. 2
A second embodiment of the sealing device according to the invention.

In Figur 1 ist ein erstes Ausführungsbeispiel einer erfindungsgemäßen Dichteinrichtung 1 zum Abdichten eines radial inneren Gaskanals 2 zwischen einem Leitschaufelkranz 4 und einem Rotor 6 einer Strömungsmaschine wie eine Gasturbine und insbesondere ein Flugtriebwerk gezeigt. Die Dichteinrichtung 1 hat einen Dichtring 8 zum Bilden eines Dichtraums 10 mit einem hinteren Abschnitt eines integralen Innenrings 12 des Leitschaufelkranzes 4. In den Dichtraum 10 taucht ein vorderer integraler Plattformüberhang 14 einer Laufschaufelreihe 16 des Rotors 6 ein, die in Richtung einer die Strömungsmaschine durchströmenden Hauptstroms stromabwärts des Leitschaufelkranzes 4 umläuft.In FIG. 1 shows a first embodiment of a sealing device 1 according to the invention for sealing a radially inner gas channel 2 between a vane ring 4 and a rotor 6 of a turbomachine such as a gas turbine and in particular an aircraft engine shown. The sealing device 1 has a sealing ring 8 for forming a sealing space 10 with a rear portion of an integral inner ring 12 of the vane ring 4. In the sealing space 10, a front integral platform overhang 14 of a rotor blade row 16 of the rotor 6, which rotates in the direction of a mainstream flowing through the turbomachine downstream of the stator blade ring 4, emerges.

Die Dichteinrichtung 1 hat zur Anbindung an den Innenring 12 einen nach außen orientierten Radialflansch 18 und der Innenring 12 hat zur Aufnahme der Dichteinrichtung 1 einen nach innen gerichteten Ringflansch 20. In dem gezeigten Ausführungsbeispiel ist die Dichteinrichtung 1 mittels einer Vielzahl von durch Bohrungen 22 des Radialflanschs 18 und des Ringflanschs 20 geführten Befestigungsmitteln 24 wie Schrauben-Muttersysteme angebunden. Der Radialflansch 18 wird dabei derart kräftig gegen den Ringflansch 20 gedrückt, dass sich zwischen diesen kein Leckagestrom ausbilden kann. Alternativ kann die Dichteinrichtung 1 an den Innenring 12 stoffschlüssig beispielsweise mittels Lötens angebunden sein. Zur vereinfachten Ausrichtung und zudem zur Erschwerung von Leckagen ist ein Anlagebereich zwischen dem Radialflansch 18 und dem Ringflansch 20 winkelig mit einer axialen Anlagebegrenzung 25 und einer radialen Anlagebegrenzung 27 versehen.The sealing device 1 has for connection to the inner ring 12 an outwardly oriented radial flange 18 and the inner ring 12 has to receive the sealing device 1 an inwardly directed annular flange 20. In the illustrated embodiment, the sealing device 1 by means of a plurality of holes 22 through the radial flange 18 and the annular flange 20 guided fasteners 24 connected as screw-nut systems. The radial flange 18 is pressed so strong against the annular flange 20 that no leakage current can form between them. Alternatively, the sealing device 1 can be bonded to the inner ring 12 by material bonding, for example by means of soldering. For ease of alignment and also for the aggravation of leaks, an abutment region between the radial flange 18 and the annular flange 20 is provided at an angle with an axial abutment boundary 25 and a radial abutment boundary 27.

Neben dem Radialflansch 18 hat die Dichteinrichtung 1 einen doppelwandigen Zylinder 26, der im montierten Zustand etwa koaxial zur Axialrichtung der Strömungsmaschine verläuft. Der Zylinder 26 hat eine Außenwandung 28 und eine Innenwandung 30, die über einen Ringbogen 32 miteinander verbunden sind. Der Zylinder 26 hat somit einen U-förmigen bzw. haarnadelartigen Querschnitt, wodurch unterschiedliche radiale thermische Dehnungen des Leitschaufelkranzes 4 zum Dichtring 8 ohne überhöhte Spannung ausgeglichen werden können. In dem gezeigten Ausführungsbeispiel ist der Dichtring 8 als ein integraler Abschnitt der Außenwandung 28 ausgebildet. Aufgrund der Koaxilität des Zylinders 26 verläuft der den Dichtring 8 bildende Abschnitt bzw. der Dichtring 8 in etwa parallel zum hinteren Abschnitt des Innenring 12.In addition to the radial flange 18, the sealing device 1 has a double-walled cylinder 26, which runs approximately coaxially with the axial direction of the turbomachine in the mounted state. The cylinder 26 has an outer wall 28 and an inner wall 30, which are connected to each other via an annular arc 32. The cylinder 26 thus has a U-shaped or hairpin-like cross section, whereby different radial thermal expansions of the vane ring 4 to the sealing ring 8 can be compensated without excessive tension. In the embodiment shown, the sealing ring 8 is formed as an integral portion of the outer wall 28. Due to the Koaxilität of the cylinder 26 of the sealing ring 8 forming portion or the sealing ring 8 extends approximately parallel to the rear portion of the inner ring 12th

Die den Dichtring 8 bildende Außenwandung 28 erstreckt sich ausgehend vom Radialflansch 18 in eine erste Richtung, und zwar gemäß der Darstellung in Figur 1 stromabwärts, und die Innenwandung 30 erstreckt sich in eine Gegenrichtung, und zwar gemäß der Darstellung in Figur 1 stromaufwärts des Hauptstroms. Die Innenwandung 30 ist radial innen zur Außenwandung 28 angeordnet und weist einen radial nach außen versetzten Wandungsabschnitt 34 auf, der etwa bis zur radialen Höhe der Außenwandung 28 verläuft. Der Wandungsabschnitt 34 geht in einen radial innen Ringsteg 36 über, der in einen stromabwärts gerichteten inneren Körperabschnitt 38 übergeht. Hierdurch weist die Dichteinrichtung 1 einen in etwa S-förmigen Querschnitt auf.The outer wall 28 forming the sealing ring 8 extends starting from the radial flange 18 in a first direction, as shown in FIG FIG. 1 downstream, and the inner wall 30 extends in an opposite direction, as shown in FIG FIG. 1 upstream of the main stream. The inner wall 30 is arranged radially inward to the outer wall 28 and has a radially outwardly offset wall portion 34 which extends approximately to the radial height of the outer wall 28. The wall portion 34 goes into a radially inwardly annular ridge 36 via, which merges into a downstream inner body portion 38. As a result, the sealing device 1 has an approximately S-shaped cross-section.

Der innere Körperabschnitt 38 ist radial innen zur Innenwandung 30 angeordnet und endet kurz vor einer axialen Position des Ringbogens 32. In dem gezeigten Ausführungsbeispiel ist er stufenförmig ausgeführt und in seiner einer Rotortrommel 39 zugewandten Seite mit einer Dichtstruktur bzw. Einlaufstruktur 40 versehen. Die Dichtstruktur 40 wirkt in Kombination mit rotorseitigen Dichtfins 42 als eine Labyrinthdichtung, mittels der ein Umströmen des Leitschaufelkranzes 4 im Bereich seiner der Rotortrommel 29 zugewandten Schaufelenden verhindert wird.The inner body portion 38 is disposed radially inward of the inner wall 30 and terminates short of an axial position of the annular arc 32. In the embodiment shown, it is designed stepwise and provided in its one rotor drum 39 side facing with a sealing structure or inlet structure 40. The sealing structure 40 acts in combination with rotor-side sealing fins 42 as a labyrinth seal, by means of which a flow around the vane ring 4 in the region of its rotor drum 29 facing blade ends is prevented.

Wie im Schnitt nach Figur 1 gezeigt, hat die Dichteinrichtung 1 über seine einzelnen integralen Abschnitte - Radialflansch 18, Zylinder 26 mit Dichtring 8, Ringsteg 36 und innerer Körperabschnitt 38 - bevorzugterweise eine einheitliche Wandstärke. Die Wandstärke ist verhältnismäßig gering, wodurch die Dichteinrichtungen 1 nicht starr ist, sondern auch federnde bzw. elastische Eigenschaften aufweist. Insbesondere der Ringboden 32 und der Ringsteg 36 wirken als radiale Federelemente. Zudem ist in Figur 1 zu erkennen, dass sich der Radialflansch 18 in etwa mittig zwischen einer axialen Position des Ringstegs 36 und der axialen Position des Ringbogens 32 befindet.As on average FIG. 1 shown, the sealing device 1 via its individual integral sections - radial flange 18, cylinder 26 with sealing ring 8, ring land 36 and inner body portion 38 - preferably a uniform wall thickness. The wall thickness is relatively low, whereby the sealing means 1 is not rigid, but also has resilient or elastic properties. In particular, the ring bottom 32 and the annular web 36 act as radial spring elements. Moreover, in FIG. 1 it can be seen that the radial flange 18 is located approximately centrally between an axial position of the annular web 36 and the axial position of the annular arc 32.

Bevorzugterweise wird die Dichteinrichtung 1 generativ hergestellt, beispielsweise mittels eines Lasersinterverfahrens oder eines selektiven Laserschmelzverfahrens. Die Dichteinrichtung 1 wird somit bevorzugterweise als ein Einzelteil in einem einzigen Verfahren hergestellt.Preferably, the sealing device 1 is produced generatively, for example by means of a laser sintering process or a selective laser melting process. The sealing device 1 is thus preferably produced as a single part in a single process.

In Figur 2 ist ein zweites Ausführungsbeispiel der erfindungsgemäßen Dichteinrichtung 1 einer Strömungsmaschine gezeigt. Dieses Ausführungsbeispiel hat ebenfalls einen Dichtring 8, einen Radialflansch 18, einen im montierten Zustand zur Axialrichtung der Strömungsmaschine koaxial verlaufenden doppelwandigen Zylinder 26, einen Ringsteg 36 und eine Dichtstruktur 40.In FIG. 2 a second embodiment of the sealing device 1 of a flow machine according to the invention is shown. This exemplary embodiment likewise has a sealing ring 8, a radial flange 18, a double-walled cylinder 26 running coaxially in the mounted state relative to the axial direction of the turbomachine, an annular web 36 and a sealing structure 40.

Im wesentlichen Unterschied zum ersten Ausführungsbeispiel nach Figur 1 erstreckt sich bei diesem Ausführungsbeispiel eine Außenwandung 28 des Zylinders 26 stromaufwärts eines die Strömungsmaschine durchströmenden Hauptstroms und eine über einen Ringbogen 32 mit der Außenwandung 28 verbundene Innenwandung 30 des Zylinders 26 stromabwärts eines die Strömungsmaschine durchströmenden Hauptstroms.Essentially difference from the first embodiment according to FIG. 1 extends in this embodiment, an outer wall 28 of the cylinder 26 upstream of a mainstream flowing through the turbomachine and a via an annular arc 32 with the Außenwandung 28 connected inner wall 30 of the cylinder 26 downstream of a mainstream flowing through the turbomachine.

Im weiteren wesentlichen Unterschied ist der Dichtring 8 bei diesem Ausführungsbeispiel nicht als integraler Abschnitt der Außenwandung 28 gebildet, sondern als ein integraler Abschnitt, der sich von einem freien Ende der Innenwandung 30 nach vorne erstreckt. In dem gezeigten Ausführungsbeispiel ist der Dichtring 8 stufenförmig mit einer bezogen auf die Innenwandung 30 radial nach außen auf eine radiale Höhe der Außenwandung 28 liegenden freien Umfangskante 46 versehen. Bevorzugterweise verläuft der Dichtring 8 mit seinem nach außen versetzten und die Umfangskante 46 bildenden Ringabschnitt 48 etwa parallel zum zum hinteren Abschnitt des Innenring 12 des Leitschaufelkranzes 4.In a further significant difference, the sealing ring 8 is not formed in this embodiment as an integral portion of the outer wall 28, but as an integral portion which extends from a free end of the inner wall 30 to the front. In the exemplary embodiment shown, the sealing ring 8 is provided in a stepped manner with a free peripheral edge 46 lying radially outwards relative to the inner wall 30 to a radial height of the outer wall 28. Preferably, the sealing ring 8 extends with its outwardly offset and the peripheral edge 46 forming annular portion 48 approximately parallel to the rear portion of the inner ring 12 of the vane ring 4th

Im weiteren wesentlichen Unterschied hat die Dichteinrichtung 1 gemäß dem Ausführungsbeispiel nach Figur 2 neben einem sich von einem Ringsteg 36 stromaufwärts erstreckenden inneren Körperabschnitt 38 einen sich stromaufwärts erstreckenden inneren Körperabschnitt 50, die zusammen mit einer durchgehenden Dichtstruktur 40 versehen sind.In another essential difference, the sealing device 1 according to the embodiment according to FIG. 2 in addition to an inner body portion 38 extending upstream from an annular ridge 36, an upstream extending inner body portion 50, which are provided together with a continuous sealing structure 40.

Wie im Schnitt nach Figur 2 gezeigt, hat auch die Dichteinrichtung 1 nach Figur 2 bevorzugterweise eine über seine einzelnen integralen Abschnitte - Radialflansch 18, Zylinder 26 mit Dichtring 8, Ringsteg 36 und innere Körperabschnitte 38, 50 - einheitliche verhältnismäßig geringe Wandstärke und ist somit in gewissen Grenzen federelastisch. Insbesondere der Ringboden 32 und der Ringsteg 36 wirken dabei als radiale Federelemente. Zudem ist in Figur 2 zu erkennen, dass sich der Radialflansch 18 in etwa mittig zwischen einer axialen Position des Ringbogens 32 und einer axialen Position der freien Umfangskante 46 des Dichtrings 8 befindet.As on average FIG. 2 shown, the sealing device 1 after FIG. 2 preferably a uniform relatively small wall thickness over its individual integral sections - radial flange 18, cylinder 26 with sealing ring 8, annular web 36 and inner body sections 38, 50 - and is thus resilient under certain limits. In particular, the ring bottom 32 and the annular web 36 act as radial spring elements. Moreover, in FIG. 2 to recognize that the radial flange 18 is located approximately centrally between an axial position of the annular arc 32 and an axial position of the free peripheral edge 46 of the sealing ring 8.

Selbstverständlich kann durch die Dichteinrichtung 1 auch eine vordere Fischmauldichtung und somit ein nabenseitiger Dichtraum zwischen einer stromaufwärtigen bzw. vorderen Laufschaufelreihe und dem Leitschaufelkranz 4 gebildet werden. Bei der Zeichnung gemäß Figur 1 würde der vordere Dichtraum zwischen dem inneren Wandungsabschnitt 34 und dem äußeren Innenring 12 gebildet sein, wobei dann die vordere Leitschaufelreihe mit einem hinterem Plattformringüberhang in diesen vorderen Dichtraum eintaucht.Of course, by the sealing device 1, a front Fischmauldichtung and thus a hub-side sealing space between an upstream or front blade row and the vane ring 4 are formed. In the drawing according to FIG. 1 would the front sealing space between the inner wall portion 34 and the outer inner ring 12 may be formed, in which case the front guide blade row is immersed with a rear platform ring overhang in this front sealing space.

Offenbart ist eine Dichteinrichtung zum Abdichten eines radial inneren Gaskanals zwischen einem Leitschaufelkranz und einem Rotor einer Strömungsmaschine, wobei die Dichteinrichtung einen Dichtring zum Bilden eines Dichtraums mit einem in Richtung einer Hauptströmung betrachtet hinteren Abschnitt eines integralen Innenrings des Leitschaufelkranzes hat, in den ein vorderer Plattformüberhangring einer stromabwärtigen Laufschaufelreihe eintaucht, und wobei die Dichteinrichtung einen äußeren Radialflansch zur Anbindung an den integralen Innenring des Leitschaufelkranzes und einen doppelwandigen Zylinder mit einer in eine erste Richtung orientierten Außenwandung und mit einer in eine Gegenrichtung orientierten Innenwandung hat, die über einen Ringbogen miteinander verbunden sind, wobei der Radialflansch in die Außenwandung des Zylinders übergeht und der Zylinder den Dichtring bildet, sowie eine Strömungsmaschine.Disclosed is a sealing device for sealing a radially inner gas channel between a vane ring and a rotor of a turbomachine, the sealing device having a sealing ring for forming a sealing space with a directed towards a main flow rear portion of an integral inner ring of the vane ring into which a front platform overhang ring a immersed downstream row of blades, and wherein the sealing means has an outer radial flange for connection to the integral inner ring of the vane ring and a double-walled cylinder having a oriented in a first direction outer wall and with an oriented in an opposite direction inner wall, which are interconnected via a ring arc the radial flange merges into the outer wall of the cylinder and the cylinder forms the sealing ring, as well as a turbomachine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Dichteinrichtungsealing device
22
innerer Gaskanalinner gas channel
44
Leitschaufelkranzvane ring
66
Rotorrotor
88th
Dichtringseal
1010
Dichtraumtight space
1212
Innenringinner ring
1414
PlattformüberhangringDeck overhang ring
1616
LaufschaufelreiheBlade row
1818
Radialflanschradial flange
2020
Ringflanschannular flange
2222
Bohrungdrilling
2424
Befestigungsmittelfastener
2525
Anlagebereichplant area
2626
Zylindercylinder
2828
Außenwandungouter wall
3030
Innenwandunginner wall
3232
Ringbogenring arc
3434
Wandungsabschnittwall section
3636
Ringstegring land
3838
innerer Körperabschnittinner body section
3939
Rotortrommelrotor drum
4040
Dichtstruktursealing structure
4242
Dichtfinsealing fin
4444
Segmentsegment
4646
Umfangskanteperipheral edge of
4848
Ringabschnittring section
5050
innerer Körperabschnittinner body section

Claims (8)

Dichteinrichtung (1) zum Abdichten eines radial inneren Gaskanals (2) zwischen einem Leitschaufelkranz (4) und einem Rotor (6) einer Strömungsmaschine, wobei die Dichteinrichtung (1) einen Dichtring (8) zum Bilden eines Dichtraums (10) mit einem in Richtung einer Hauptströmung betrachtet hinteren Abschnitt eines integralen Innenrings (12) des Leitschaufelkranzes (4) hat, in den ein vorderer Plattformüberhangring (14) einer stromabwärtigen Laufschaufelreihe (16) eintaucht, und wobei die Dichteinrichtung (1) einen äußeren Radialflansch (18) zur Anbindung an den integralen Innenring (12) und einen doppelwandigen Zylinder (26) mit einer in eine erste Richtung orientierten Außenwandung (28) und mit einer in eine Gegenrichtung orientierten Innenwandung (30) hat, die über einen Ringbogen (32) miteinander verbunden sind, wobei der Radialflansch (18) in die Außenwandung (28) übergeht und der Zylinder (26) den Dichtring (8) bildet,
dadurch gekennzeichnet, dass die Innenwandung (30) über einen Ringsteg (36) in wenigstens einen parallel zur ersten Richtung bzw. zur Gegenrichtung orientierten inneren Körperabschnitt (38,50) zur radial inneren Aufnahme einer Dichtstruktur (40) übergeht,
wobei die Dichteinrichtung (1) über ihre einzelnen, integral miteinander ausgebildeten Abschnitte eine einheitliche, vorzugsweise verhältnismäßig geringe, Wandstärke aufweist, so dass die Dichteinrichtung (1) in gewissen Grenzen federelastisch ist, wobei insbesondere der Ringbogen (32) und der Ringsteg (36) als radiale Federelemente wirken.Sealing device (1) for sealing a radially inner gas channel (2) between a vane ring (4) and a rotor (6) of a turbomachine, wherein the sealing device (1) has a sealing ring (8) for forming a sealing space (10) with a in direction a main flow seen in the rear portion of an integral inner ring (12) of the vane ring (4), in which a front platform overhang ring (14) of a downstream blade row (16) is immersed, and wherein the sealing means (1) has an outer radial flange (18) for connection to the integral inner ring (12) and a double - walled cylinder (26) having an outer wall (28) oriented in a first direction and an inner wall (30) oriented in an opposite direction and interconnected by an annular arc (32) Radial flange (18) merges into the outer wall (28) and the cylinder (26) forms the sealing ring (8),
characterized in that the inner wall (30) via an annular web (36) in at least one parallel to the first direction or to the opposite direction oriented inner body portion (38,50) for radially inner recording of a sealing structure (40) passes,
wherein the sealing device (1) has a uniform, preferably relatively small, wall thickness via its individual, integrally formed sections, so that the sealing device (1) is resilient under certain limits, wherein in particular the annular arc (32) and the annular web (36) act as radial spring elements. Dichteinrichtung nach Anspruch 1, wobei die Außenwandung (28) den Dichtring (8) bildet und die Außenwandung (28) stromabwärts und die Innenwandung (30) stromaufwärts gerichtet ist.Sealing device according to claim 1, wherein the outer wall (28) forms the sealing ring (8) and the outer wall (28) is directed downstream and the inner wall (30) upstream. Dichteinrichtung nach Anspruch 2, wobei der wenigstens eine innere Körperabschnitt (38) von dem Ringsteg (36) betrachtet stromabwärts gerichtet ist.The sealing device of claim 2, wherein said at least one inner body portion (38) is directed downstream from said annular land (36). Dichteinrichtung nach Anspruch 1, wobei der Dichtring (8) an der Innenwandung (30) ausgebildet ist und die Außenwandung (28) stromaufwärts und die Innenwandung (30) stromabwärts gerichtet ist.Sealing device according to claim 1, wherein the sealing ring (8) on the inner wall (30) is formed and the outer wall (28) upstream and the inner wall (30) is directed downstream. Dichteinrichtung nach Anspruch 4, wobei ein innerer Körperabschnitt (38) von dem Ringsteg (36) betrachtet stromabwärts gerichtet ist und ein anderer innerer Körperabschnitt (50) von dem Ringsteg (36) betrachtet stromabwärts gerichtet ist.The sealing device of claim 4, wherein an inner body portion (38) is directed downstream from said annular land (36) and another inner body portion (50) faces downstream from said annular land (36). Dichteinrichtung nach einem der vorhergehenden Ansprüche, wobei der Radialflansch (18) in Axialrichtung betrachtet etwa mittig der Dichteinrichtung (1) angeordnet ist.Sealing device according to one of the preceding claims, wherein the radial flange (18) viewed in the axial direction approximately centrally of the sealing device (1) is arranged. Dichteinrichtung nach einem der vorhergehenden Ansprüche, wobei die Dichteinrichtung (1) generativ hergestellt ist.Sealing device according to one of the preceding claims, wherein the sealing device (1) is produced generatively. Strömungsmaschine mit zumindest einer Dichteinrichtung (1) nach einem der vorhergehenden Ansprüche.Turbomachine with at least one sealing device (1) according to one of the preceding claims.
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US20150001811A1 (en) 2015-01-01
US9664059B2 (en) 2017-05-30
ES2684775T3 (en) 2018-10-04

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