EP2824279A1 - Flow engine, guide blade and rotor blade - Google Patents

Flow engine, guide blade and rotor blade Download PDF

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Publication number
EP2824279A1
EP2824279A1 EP13175726.2A EP13175726A EP2824279A1 EP 2824279 A1 EP2824279 A1 EP 2824279A1 EP 13175726 A EP13175726 A EP 13175726A EP 2824279 A1 EP2824279 A1 EP 2824279A1
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EP
European Patent Office
Prior art keywords
ring
blade
axial
row
overhang
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
EP13175726.2A
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German (de)
French (fr)
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EP2824279B1 (en
Inventor
Christoph Lauer
Markus Hirschmann
Yannick Dr. Muller
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MTU Aero Engines AG
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MTU Aero Engines AG
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Priority to ES13175726T priority Critical patent/ES2724533T3/en
Priority to EP13175726.2A priority patent/EP2824279B1/en
Publication of EP2824279A1 publication Critical patent/EP2824279A1/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
    • F01D11/001—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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing

Definitions

  • the invention relates to a turbomachine according to the preamble of patent claim 1, a vane and a blade.
  • a turbomachine is shown with a sealing device which is formed as a labyrinth seal between a radially outer stator ring and a radially inner rotor ring.
  • the rings are in axial overlap, wherein the rotor ring in addition to its radially outwardly directed end portion to approximately its half axial extent has a circumferential radially outwardly directed sealing ridge.
  • the stator ring has a radially inwardly directed end portion.
  • FIG. 2 shows a turbomachine with a sealing device between a stationary airfoil row arranged in a turbine intermediate housing and a subsequent blade row.
  • the object of the invention is to provide a turbomachine having an alternative sealing means for sealing an axial gap between a series of airfoils and a downstream blade row.
  • the sealing device has a downstream-oriented guide vane-side axial ring, which extends axially beyond a platform ring trailing edge of the airfoil row and has a radially outwardly directed end portion.
  • the sealing device has an upstream platform ring overhang, which is arranged on the blade row and having a radially inwardly directed end portion, wherein the axial ring is arranged radially inward to the platform ring overhang and forms an axial overlap with this.
  • the front platform ring overhang follows, at least in sections, an ideal flow pattern of the hot gas over the rotor blade-side platform ring.
  • the formation of the airfoil series without a downstream or rear platform ring overhang in conjunction with the radially inwardly running rear hook-like axial ring and the axially outer overlap with the Axialring located radially outer front hook-like platform ring overhang causes a sealing space or a vortex zone in which / the incoming hot gas with a high tangential velocity component is applied.
  • the inflowing hot gas is swirled and thereby made much more difficult or prevented at its entry into the cooling channel.
  • the sealing space acts as a damping area between the hot gas duct and the inner cooling channel, whereby pressure differences between the hot gas duct and the inner cooling channel are weakened, whereby also a hot gas from the hot gas duct into the inner cooling channel is difficult.
  • the sealing device according to the invention allows large axial and radial relative movements of the rotor and the stator to each other in comparison to conventional Fischmauldichtitch at a small axial gap. Due to the fact that the front platform ring overhang follows, at least in sections, an ideal flow course of the hot gas over the blade row side platform ring, in the region of the platform overhang in the hot gas channel, eddies are prevented or substantially reduced.
  • the sealing device is preferably arranged on the turbine side of the turbomachine such as a gas turbine and in particular an aircraft engine.
  • the airfoil series is a vane row in a low-pressure turbine of the turbomachine.
  • the airfoil series can also consist of a plurality of blade profiles arranged in a turbine intermediate housing between a high-pressure turbine and a low-pressure turbine.
  • the end portions are spaced apart in the radial direction. As a result, a radial gap is essentially created, can be blown through the cooling air from the cooling passage in the sealing chamber.
  • the end portions terminate at the same radial height.
  • an axial gap is substantially created, can be blown through the cooling air from the cooling passage in the sealing chamber.
  • the end portion of the axial ring has a greater radial extent than the end portion of the front platform ring overhang.
  • the end portion of the rotating platform ring overhang is shortened in this embodiment compared to the end portion of the fixed axial ring.
  • the end portions of the platform ring overhang are stabilized by the short radial extent, which prevents the introduction of disturbing vibrations in the rotor by the rotating end portions.
  • the end portions are parallel and oriented radially offset from one another.
  • the end portions are orthogonal to the axial direction of the turbomachine. Due to the parallelism, an axial component of the radial gap is kept constant despite different thermal radial expansion behavior of the axial ring and the platform ring overhang or of the stator and of the rotor.
  • the end portions are set to each other.
  • the end portion of the axial ring is inclined downstream in the axial direction and the end portion of the front platform ring overhang is orthogonal to the axial direction. Due to the inclination or inclination of the gap between the cooling chamber and the sealing space can be opened.
  • a guide vane according to the invention for a turbomachine according to the invention has a downstream-oriented axial overhang which extends axially beyond a platform trailing edge and has a radially outwardly directed end portion.
  • Such a guide vane allows the formation of a row of guide vanes into which the preferred sealing device for preventing fuel gas is integrated in sections.
  • a blade according to the invention for a turbomachine according to the invention has an upstream front platform overhang, which has a radially inwardly directed end portion. Such a blade allows the formation of a blade row, in which the preferred sealing means for preventing Schugaseizugs is partially integrated.
  • FIG. 1 a longitudinal section through a turbomachine in the region of a flow profile row 1 and a row of airfoils 1 downstream flow profile row 2 is shown.
  • the flow profile row is a row of guide vanes.
  • the guide blade row 1 and the blade row 2 have a plurality of blades 35, 36, which are arranged side by side in the circumferential direction of the turbomachine and their respective blade 4, 6 is arranged in the hot gas duct 8 of the turbomachine.
  • the turbomachine is a gas turbine and in particular an aircraft engine.
  • the guide vane row 1 and the blade row 2 are arranged in particular on the turbine side and, for example, in the low-pressure turbine of the turbomachine.
  • the hot gas channel 8 is from a hot gas stream as shown in FIG. 2 flows through from left to right. It is bounded radially on the inside by a guide-row-side platform ring 10 and by a rotor blade-side platform ring 12. Radially inside the hot gas duct 8, a cooling space 14 is formed, which is flowed through by a cooling air flow.
  • a sealing device 18 is arranged in the axial gap between the guide vane row 1 and the blade row 2.
  • FIG. 1 shown first embodiment of the sealing device 18 forms a ring-like sealing space 20.
  • the sealing space 20 is in the in FIG. 1 shown embodiment via an annular axial outer gap 21 to the hot gas channel 8 and via an annular axial inner gap 23 to the cooling channel 14.
  • the hot gas partial stream 16 enters the sealing space 20 and is swirled in this.
  • a partial cooling air flow 22nd injected, which lays on a hot gas partial flow vortex 25 in the sealing chamber 20 and exits into the hot gas channel 8.
  • the sealing device 18 has an opposite to a guide vane row-side front platform ring trailing edge 24 radially inwardly disposed axial ring 26 which is oriented downstream in the direction of the blade row 2 and has a radially outwardly directed end portion 28.
  • the sealing device 18 has a blade row-side front platform ring overhang 30, which is oriented downstream in the direction of the guide blade row 1 and has a radially inwardly directed end portion 32.
  • the circumferential end portions 28, 32 thus have in opposite radial directions, wherein they face each other.
  • the axial ring 26 and the platform ring overhang 30 are in axial overlap. They are in the in FIG. 1 shown embodiment in axial overlap that the sealing space 20 is not open over its entire axial extent to the hot gas channel 8, but only in the area near the platform ring trailing edge 24th
  • the axial ring 26 extends with a cylindrical annular portion 34 in the axial direction of the turbomachine and is arranged radially inward to the platform ring overhang 30. Its end portion 28 extends from the ring portion 34 and is made inclined downstream, extending radially outwardly. The end portion 28 thus points in the direction of the front platform ring overhang 30.
  • the front platform ring overhang 30 follows in the embodiment shown with a ring portion 37 an ideal flow of the hot gas over the blade row side platform ring 12. He goes for this purpose on a stepless in the platform 12 and has viewed in the flow direction a funnel-shaped opening contour.
  • the end portion 32 of the front platform ring overhang 30 extends from the ring portion 37. It is orthogonal to the axial direction and thus orthogonal to the ring portion 34 of the axial ring 26, extending radially inwardly.
  • the end portion 32 has a short Radial extent than the end portion 28 of the axial ring 26. In the illustrated embodiment, it has such a radial extent that it ends at or approximately at the same radial height as the end portion 28 of the axial ring 26. Downstream forms the end portion 32 of the platform ring overhang 30 together with the end portion 28 of the axial ring 26, the inner gap 23, the here in FIG. 1 almost an axial gap.
  • FIG. 2 shown embodiment of a sealing device 18 between a stator blade 1 and a downstream blade row 2 of a turbomachine to prevent a hot gas inlet 16 from a radially outer hot gas channel 8 in a radially inner cooling channel 14 to form a sealing space 20 are essentially different from the embodiment according to FIG. 1 both end portions 28, 32 oriented orthogonal to the axial ring portion 34 and to the axial direction of the turbomachine.
  • the end sections 28, 32 are aligned almost parallel to one another.
  • a ring-like inner gap 23 for injecting a cooling air partial flow 22 into the sealing space 20 has a greater axial component than a radial component and thus is virtually a radial gap.
  • end sections 28, 32 are substantially different from a guide blade-side platform ring trailing edge 24 in that a ring-like axial outer gap 21 extends virtually over the entire axial extent of the axial ring 26 and the sealing space 20 thus opens to the hot gas channel 8 virtually over its entire axial extent is.
  • a respective vane 35 of the vane row 1 is formed without a rear platform overhang.
  • the vane 35 has in each case one to a rear platform edge radially inwardly positioned axial projection with a radially outwardly directed end portion.
  • the adjacent axial projections form the axial ring 26, wherein the end regions form the peripheral end section 28.
  • FIG. 3 a blade 36 according to the invention for the formation of an aforementioned blade row 2 is shown.
  • the blade 36 has seen in the direction of flow of a hot gas, a front platform overhang 38 with a radially inwardly directed end portion 40.
  • the front platform overhang 38 follows an ideal flow of the hot gas through a paddle platform 42.
  • the front platform overhang 38 is steplessly into the paddle platform 42 and is in accordance with the blade platform 42 ascending inclined in the flow direction.
  • the in FIG. 3 shown blade 36 a rear platform overhang 44 which is aligned almost axially to the axial direction.
  • the adjacent front platform overhangs 38 form the front platform ring overhang 30, wherein the end portions 40 form the peripheral end portion 32.
  • a turbomachine having sealing means for preventing hot gas ingress through an axial gap between a series of airfoils and a blade row from a hot gas passage into a cooling passage, the sealing means having a downstream orifice-side axial ring extending axially beyond a platform ring trailing edge of the airfoil row and a radial one has an outwardly directed end portion, and an upstream blade-side platform ring overhang having a radially inwardly directed end portion, wherein the Axialring is arranged radially inwardly to the platform ring overhang and forms an axial overlap therewith, wherein the front platform ring overhang at least partially an ideal flow of the Hot gas over the blade row side platform ring follows, as well as a vane and a blade.

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

Abstract

Offenbart ist eine Strömungsmaschine, mit einer Dichteinrichtung zum Verhindern eines Heißgaseinzugs durch einen Axialspalt zwischen einer Strömungsprofilreihe und einer Laufschaufelreihe aus einem Heißgaskanal in einen Kühlkanal, wobei die Dichteinrichtung einen stromabwärts orientierten leitschaufelseitigen Axialring hat, der sich axial über eine Plattformringhinterkante der Strömungsprofilreihe erstreckt und einen radial nach außen gerichteten Endabschnitt hat, und einen stromaufwärts gerichteten laufschaufelseitigen Plattformringüberhang aufweist, der einen radial nach innen gerichteten Endabschnitt aufweist, wobei der Axialring radial innen zum Plattformringüberhang angeordnet ist und mit diesem eine axiale Überlappung bildet, wobei der vordere Plattformringüberhang zumindest abschnittsweise einem idealen Strömungsverlauf des Heißgases über den laufschaufelreihenseitigen Plattformring folgt, sowie eine Leitschaufel und eine Laufschaufel.Disclosed is a turbomachine having sealing means for preventing hot gas ingress through an axial gap between a series of airfoils and a blade row from a hot gas passage into a cooling passage, the sealing means having a downstream orifice-side axial ring extending axially beyond a platform ring trailing edge of the airfoil row and a radial one has an outwardly directed end portion, and an upstream blade-side platform ring overhang having a radially inwardly directed end portion, wherein the Axialring is arranged radially inwardly to the platform ring overhang and forms an axial overlap therewith, wherein the front platform ring overhang at least partially an ideal flow of the Hot gas over the blade row side platform ring follows, as well as a vane and a blade.

Description

Die Erfindung betrifft eine Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1, eine Leitschaufel sowie eine Laufschaufel.The invention relates to a turbomachine according to the preamble of patent claim 1, a vane and a blade.

Um bei einer Strömungsmaschine wie einer Gasturbine einen Heißgaseinzug eines Heißgases aus einem radial äußeren Heißgaskanal in einen radial inneren Kühlkanal durch einen Axialspalt zwischen einer Strömungsprofilreihe bzw. Leitschaufelreihe und einer stromabwärtigen Laufschaufelreihe zu verhindern, werden sogenannte Fischmauldichtungen verwendet, bei denen ein umlaufender Rotorring der Laufschaufelreihe in einen ringförmigen Dichtraum läuft, der von einem radial inneren Statorring und einem radial äußeren Statorring der Leitschaufelreihe begrenzt wird. Im Dichtraum bilden sich Wirbel aus, die das Eindringen von Heißgas aus dem Heißgaskanal in den Kühlkanal verhindern sollen. Der innere Statorring kann wie in der US 2010172749 A1 gezeigt als integrales Bauteil mit dem äußeren Statorring ausgebildet sein oder wie in der DE 2847012 A1 gezeigt als separates Bauteil.In order to prevent a hot gas from a radially outer hot gas channel in a radially inner cooling channel through an axial gap between a series of airfoils and a downstream blade row in a turbomachine such as a gas turbine, so-called Fischmauldichtungen be used in which a rotating rotor ring of the blade row in an annular sealing space runs, which is bounded by a radially inner stator ring and a radially outer stator ring of the row of guide vanes. In the sealing space vortex form, which should prevent the ingress of hot gas from the hot gas channel into the cooling channel. The inner stator ring can as in the US 2010172749 A1 shown formed as an integral component with the outer stator ring or as in the DE 2847012 A1 shown as a separate component.

Aus der US 7540709 B1 ist eine Strömungsmaschine mit einer Dichteinrichtung zwischen einer Leitschaufelreihe und einer Laufschaufelreihe bekannt, die einen radial inneren hakenartigen Statorring und einen radial äußeren hakenartigen Rotorring aufweist. Die beiden Ringe befinden sich in axialer Überlappung, wobei zwischen ihnen aufgrund ihrer hakenartigen Ausbildung ein Dichtraum gebildet ist.From the US 7540709 B1 is a turbomachine with a sealing device between a row of vanes and a blade row is known, which has a radially inner hook-like stator ring and a radially outer hook-like rotor ring. The two rings are in axial overlap, with a sealing space formed between them due to their hook-like design.

In der US 8075256 B2 ist eine Strömungsmaschine mit einer Dichteinrichtung gezeigt, die als eine Labyrinthdichtung zwischen einem radial äußeren Statorring und einem radial innen laufenden Rotorring ausgebildet ist. Die Ringe befinden sich in axialer Überlappung, wobei der Rotorring zusätzlich zu seinem radial nach außen gerichteten Endabschnitt auf ungefähr seiner halben axialen Erstreckung einen umlaufenden radial nach außen gerichteten Dichtsteg hat. Der Statorring hat einen radial nach innen gerichteten Endabschnitt.In the US 8075256 B2 a turbomachine is shown with a sealing device which is formed as a labyrinth seal between a radially outer stator ring and a radially inner rotor ring. The rings are in axial overlap, wherein the rotor ring in addition to its radially outwardly directed end portion to approximately its half axial extent has a circumferential radially outwardly directed sealing ridge. The stator ring has a radially inwardly directed end portion.

Aus der EP 2573329 A2 ist eine Strömungsmaschine mit einer Dichteinrichtung zwischen einer in einem Turbinenzwischengehäuse angeordneten feststehenden Strömungsprofilreihe und einer nachfolgenden Laufschaufelreihe gezeigt.From the EP 2573329 A2 FIG. 2 shows a turbomachine with a sealing device between a stationary airfoil row arranged in a turbine intermediate housing and a subsequent blade row.

Aufgabe der Erfindung ist es, eine Strömungsmaschine zu schaffen, die eine alternative Dichteinrichtung zum Abdichten eines Axialspaltes zwischen einer Strömungsprofilreihe und einer stromabwärtigen Laufschaufelreihe aufweist. Zudem ist es Aufgabe der Erfindung, eine Leitschaufel und eine Laufschaufel für eine derartige Strömungsmaschine zu schaffen.The object of the invention is to provide a turbomachine having an alternative sealing means for sealing an axial gap between a series of airfoils and a downstream blade row. In addition, it is an object of the invention to provide a vane and a blade for such a turbomachine.

Diese Aufgabe wird gelöst durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 1, durch eine Leitschaufel mit den Merkmalen des Patentanspruchs 7 und durch eine Laufschaufel mit den Merkmalen des Patentanspruchs 8.This object is achieved by a turbomachine having the features of patent claim 1, by a guide blade having the features of patent claim 7 and by a moving blade having the features of patent claim 8.

Eine erfindungsgemäße Strömungsmaschine mit einer Strömungsprofilreihe und einer zur Strömungsprofilreihe stromabwärtigen Laufschaufelreihe, zwischen denen ein radial innerer Kühlkanal gebildet ist, wobei die Strömungsprofilreihe und die Laufschaufelreihe jeweils einen Plattformring aufweisen, der einen radial äußeren Heißgaskanal begrenzt, hat eine Dichteinrichtung zum Verhindern eines Heißgaseinzuges durch einen Axialspalt zwischen den Reihen aus dem Heißgaskanal in den Kühlkanal. Erfindungsgemäß hat die Dichteinrichtung einen stromabwärts orientierten leitschaufelseitigen Axialring, der sich axial über eine Plattformringhinterkante der Strömungsprofilreihe erstreckt und einen radial nach außen gerichteten Endabschnitt hat. Zudem hat die Dichteinrichtung einen stromaufwärts gerichteten Plattformringüberhang, der an der Laufschaufelreihe angeordnet ist und einen radial nach innen gerichteten Endabschnitt aufweist, wobei der Axialring radial innen zum Plattformringüberhang angeordnet ist und mit diesem eine axial Überlappung bildet. Dabei folgt der vordere Plattformringüberhang zumindest abschnittsweise einem idealen Strömungsverlauf des Heißgases über den laufschaufelreihenseitigen Plattformring.A turbomachine according to the invention with a flow profile row and a blade row downstream of the airfoil row, between which a radially inner cooling channel is formed, the airfoil row and the blade row each having a platform ring defining a radially outer hot gas channel, has a sealing means for preventing hot gas intake through an axial gap between the rows of the hot gas duct in the cooling channel. According to the invention, the sealing device has a downstream-oriented guide vane-side axial ring, which extends axially beyond a platform ring trailing edge of the airfoil row and has a radially outwardly directed end portion. In addition, the sealing device has an upstream platform ring overhang, which is arranged on the blade row and having a radially inwardly directed end portion, wherein the axial ring is arranged radially inward to the platform ring overhang and forms an axial overlap with this. In this case, the front platform ring overhang follows, at least in sections, an ideal flow pattern of the hot gas over the rotor blade-side platform ring.

Die Ausbildung der Strömungsprofilreihe ohne einen stromabwärtigen bzw. hinteren Plattformringüberhang in Verbindung mit dem zu ihrem Plattformring radial innen laufenden hinteren hakenartigen Axialring und dem mit sich in axialer Überlappung mit dem Axialring befindenden radial äußeren vorderen hakenartigen Plattformringüberhang bewirkt einen Dichtraum bzw. eine Wirbelzone, in dem/die einströmendes Heißgas mit einer hohen tangentialen Geschwindigkeitskomponente beaufschlagt wird. Das einströmende Heißgas wird verwirbelt und hierdurch an seinem Einzug in den Kühlkanal wesentlich erschwert bzw. unterbunden. Zudem wirkt der Dichtraum als ein Dämpfungsbereich zwischen dem Heißgaskanal und dem inneren Kühlkanal, wodurch Druckunterschiede zwischen dem Heißgaskanal und dem inneren Kühlkanal abgeschwächt werden, wodurch ebenfalls ein Heißgaseinzug aus dem Heißgaskanal in den inneren Kühlkanal erschwert wird. Des Weiteren ermöglicht die erfindungsgemäße Dichteinrichtung im Vergleich zu herkömmlichen Fischmauldichtungen bei einem kleinen Axialspalt große axiale und radiale Relativbewegungen des Rotors und des Stators zueinander. Dadurch, dass der vordere Plattformringüberhang zumindest abschnittsweise einen idealen Strömungsverlauf des Heißgases über den laufschaufelreihenseitigen Plattformring folgt, werden zudem Wirbel im Bereich des Plattformüberhangs im Heißgaskanal verhindert bzw. wesentlich reduziert. Die Dichteinrichtung ist bevorzugterweise turbinenseitig der Strömungsmaschine wie eine Gasturbine und insbesondere ein Flugtriebwerk angeordnet. Beispielsweise ist die Strömungsprofilreihe eine Leitschaufelreihe in einer Niederdruckturbine der Strömungsmaschine. Allerdings kann die Strömungsprofilreihe auch aus einer Vielzahl von in einem Turbinenzwischengehäuse zwischen einer Hochdruckturbine und einer Niederdruckturbine angeordneten Schaufelprofilen bestehen.The formation of the airfoil series without a downstream or rear platform ring overhang in conjunction with the radially inwardly running rear hook-like axial ring and the axially outer overlap with the Axialring located radially outer front hook-like platform ring overhang causes a sealing space or a vortex zone in which / the incoming hot gas with a high tangential velocity component is applied. The inflowing hot gas is swirled and thereby made much more difficult or prevented at its entry into the cooling channel. In addition, the sealing space acts as a damping area between the hot gas duct and the inner cooling channel, whereby pressure differences between the hot gas duct and the inner cooling channel are weakened, whereby also a hot gas from the hot gas duct into the inner cooling channel is difficult. Furthermore, the sealing device according to the invention allows large axial and radial relative movements of the rotor and the stator to each other in comparison to conventional Fischmauldichtungen at a small axial gap. Due to the fact that the front platform ring overhang follows, at least in sections, an ideal flow course of the hot gas over the blade row side platform ring, in the region of the platform overhang in the hot gas channel, eddies are prevented or substantially reduced. The sealing device is preferably arranged on the turbine side of the turbomachine such as a gas turbine and in particular an aircraft engine. For example, the airfoil series is a vane row in a low-pressure turbine of the turbomachine. However, the airfoil series can also consist of a plurality of blade profiles arranged in a turbine intermediate housing between a high-pressure turbine and a low-pressure turbine.

Bei einem Ausführungsbeispiel sind die Endabschnitte in radialer Richtung voneinander beabstandet. Hierdurch wird im wesentlichen ein Radialspalt geschaffen, durch den Kühlluft aus dem Kühlkanal in den Dichtraum ausgeblasen werden kann.In one embodiment, the end portions are spaced apart in the radial direction. As a result, a radial gap is essentially created, can be blown through the cooling air from the cooling passage in the sealing chamber.

Bei einem anderen Ausführungsbeispiel enden die Endabschnitte auf gleicher radialer Höhe. Hierdurch wird im wesentlichen ein Axialspalt geschaffen, durch den Kühlluft aus dem Kühlkanal in den Dichtraum ausgeblasen werden kann.In another embodiment, the end portions terminate at the same radial height. As a result, an axial gap is substantially created, can be blown through the cooling air from the cooling passage in the sealing chamber.

Bevorzugterweise hat der Endabschnitt des Axialrings eine größere radiale Erstreckung als der Endabschnitt des vorderen Plattformringüberhanges. Der Endabschnitt des rotierenden Plattformringüberhangs ist bei diesem Ausführungsbeispiel im Vergleich zum Endabschnitt des feststehenden Axialrings verkürzt. Die Endabschnitte des Plattformringüberhangs sind durch die kurze radiale Erstreckung stabilisiert, wodurch eine Einleitung von störenden Schwingungen in den Rotor durch die rotierenden Endabschnitte verhindert wird.Preferably, the end portion of the axial ring has a greater radial extent than the end portion of the front platform ring overhang. The end portion of the rotating platform ring overhang is shortened in this embodiment compared to the end portion of the fixed axial ring. The end portions of the platform ring overhang are stabilized by the short radial extent, which prevents the introduction of disturbing vibrations in the rotor by the rotating end portions.

Bei einem Ausführungsbeispiel sind die Endabschnitte parallel und in radialer Richtung versetzt zueinander orientiert. Beispielsweise verlaufen die Endabschnitte orthogonal zur Axialrichtung der Strömungsmaschine. Durch die Parallelität wird eine axiale Komponente des Radialspalts trotz unterschiedlicher thermischer radialer Dehnungsverhalten des Axialrings und des Plattformringüberhangs bzw. des Stators und des Rotors konstant gehalten.In one embodiment, the end portions are parallel and oriented radially offset from one another. For example, the end portions are orthogonal to the axial direction of the turbomachine. Due to the parallelism, an axial component of the radial gap is kept constant despite different thermal radial expansion behavior of the axial ring and the platform ring overhang or of the stator and of the rotor.

Bei einem anderen Ausführungsbeispiel sind die Endabschnitte zueinander angestellt. Beispielsweise ist der Endabschnitt des Axialrings in Axialrichtung stromabwärts geneigt und der Endabschnitt des vorderen Plattformringüberhangs verläuft orthogonal zur Axialrichtung. Durch die Schrägstellung bzw. Neigung kann der Spalt zwischen dem Kühlraum und dem Dichtraum geöffnet werden.In another embodiment, the end portions are set to each other. For example, the end portion of the axial ring is inclined downstream in the axial direction and the end portion of the front platform ring overhang is orthogonal to the axial direction. Due to the inclination or inclination of the gap between the cooling chamber and the sealing space can be opened.

Eine erfindungsgemäße Leitschaufel für eine erfindungsgemäße Strömungsmaschine hat einen stromabwärts orientierten Axialüberhang, der sich axial über eine Plattformhinterkante erstreckt und einen radial nach außen gerichteten Endabschnitt aufweist. Eine derartige Leitschaufel ermöglicht die Bildung einer Leitschaufelreihe, in die die bevorzugte Dichteinrichtung zum Verhindern eines Heizgaseizugs abschnittsweise integriert ist.A guide vane according to the invention for a turbomachine according to the invention has a downstream-oriented axial overhang which extends axially beyond a platform trailing edge and has a radially outwardly directed end portion. Such a guide vane allows the formation of a row of guide vanes into which the preferred sealing device for preventing fuel gas is integrated in sections.

Eine erfindungsgemäße Laufschaufel für eine erfindungsgemäße Strömungsmaschine hat einen stromaufwärts gerichteten vorderen Plattformüberhang, der einen radial nach innen gerichteten Endabschnitt aufweist. Eine derartige Laufschaufel ermöglicht die Bildung einer Laufschaufelreihe, in die die bevorzugte Dichteinrichtung zum Verhindern eines Heizgaseizugs abschnittsweise integriert ist.A blade according to the invention for a turbomachine according to the invention has an upstream front platform overhang, which has a radially inwardly directed end portion. Such a blade allows the formation of a blade row, in which the preferred sealing means for preventing Heizgaseizugs is partially integrated.

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 stark vereinfachter schematischer Darstellungen näher erläutert. Es zeigen:

Figur 1
einen Längsschnitt durch eine erfindungsgemäße Strömungsmaschine im Bereich einer ersten beispielhaften Dichteinrichtung,
Figur 2
einen Längsschnitt durch eine erfindungsgemäße Strömungsmaschine im Bereich einer zweiten beispielhaften Dichteinrichtung, und
Figur 3
eine Seitendarstellung einer erfindungsgemäßen Laufschaufel.
In the following, preferred embodiments of the invention will be explained in more detail with reference to highly simplified schematic illustrations. Show it:
FIG. 1
a longitudinal section through a flow machine according to the invention in the region of a first exemplary sealing device,
FIG. 2
a longitudinal section through a flow machine according to the invention in the region of a second exemplary sealing device, and
FIG. 3
a side view of a blade according to the invention.

In Figur 1 ist ein Längsschnitt durch eine Strömungsmaschine im Bereich einer Strömungsprofilreihe 1 und einer zur Leitschaufelreihe 1 stromabwärtigen Strömungsprofilreihe 2 gezeigt. In dem gezeigten Ausführungsbeispiel ist die Strömungsprofilreihe eine Leitschaufelreihe. Die Leitschaufelreihe 1 sowie die Laufschaufelreihe 2 weisen eine Vielzahl von Schaufeln 35, 36 auf, die in Umfangsrichtung der Strömungsmaschine nebeneinander angeordnet sind und deren jeweiliges Schaufelblatt 4, 6 im Heißgaskanal 8 der Strömungsmaschine angeordnet ist. Die Strömungsmaschine ist eine Gasturbine und insbesondere ein Flugtriebwerk. Die Leitschaufelreihe 1 und die Laufschaufelreihe 2 sind insbesondere turbinenseitig und beispielsweise in der Niederdruckturbine der Strömungsmaschine angeordnet.In FIG. 1 a longitudinal section through a turbomachine in the region of a flow profile row 1 and a row of airfoils 1 downstream flow profile row 2 is shown. In the embodiment shown, the flow profile row is a row of guide vanes. The guide blade row 1 and the blade row 2 have a plurality of blades 35, 36, which are arranged side by side in the circumferential direction of the turbomachine and their respective blade 4, 6 is arranged in the hot gas duct 8 of the turbomachine. The turbomachine is a gas turbine and in particular an aircraft engine. The guide vane row 1 and the blade row 2 are arranged in particular on the turbine side and, for example, in the low-pressure turbine of the turbomachine.

Der Heißgaskanal 8 wird von einem Heißgasstrom gemäß der Darstellung in Figur 2 von links nach rechts durchströmt. Er ist radial innen von einem leitschaufelreihenseitigen Plattforming 10 und von einem laufschaufelreihenseitigen Plattformring 12 begrenzt. Radial innen zum Heißgaskanal 8 ist ein Kühlraum 14 gebildet, der von einem Kühlluftstrom durchströmt wird.The hot gas channel 8 is from a hot gas stream as shown in FIG FIG. 2 flows through from left to right. It is bounded radially on the inside by a guide-row-side platform ring 10 and by a rotor blade-side platform ring 12. Radially inside the hot gas duct 8, a cooling space 14 is formed, which is flowed through by a cooling air flow.

Um einen Heißgaseinzug bzw. einen Einzug eines Heißgasteilstroms 16 durch einen Axialspalt zwischen der Leitschaufelreihe 1 und der Laufschaufelreihe 2 aus dem Heißgaskanal 8 in den Kühlraum 14 zu verhindern, ist im Axialspalt zwischen der Leitschaufelreihe 1 und der Laufschaufelreihe 2 eine Dichteinrichtung 18 angeordnet.In order to prevent a hot gas inlet or an intake of a hot gas partial flow 16 through an axial gap between the guide vane row 1 and the blade row 2 from the hot gas channel 8 into the cooling space 14, a sealing device 18 is arranged in the axial gap between the guide vane row 1 and the blade row 2.

Das in Figur 1 gezeigte erste Ausführungsbeispiel der Dichteinrichtung 18 bildet einen ringartigen Dichtraum 20. Der Dichtraum 20 ist in dem in Figur 1 gezeigten Ausführungsbeispiel über einen ringartigen axialen Außenspalt 21 zum Heißgaskanal 8 und über einen ringartigen axialen Innenpalt 23 zum Kühlkanal 14 geöffnet. Durch den Außenspalt 21 tritt der Heißgasteilstrom 16 in den Dichtraum 20 ein und wird in diesem verwirbelt. Zur Wirbelführung wird gleichzeitig durch den Innenpalt 23 in den Dichtraum 20 ein Kühlluftteilstrom 22 eingeblasen, der sich auf einen Heißgasteilstromwirbel 25 im Dichtraum 20 legt und in den Heißgaskanal 8 austritt.This in FIG. 1 shown first embodiment of the sealing device 18 forms a ring-like sealing space 20. The sealing space 20 is in the in FIG. 1 shown embodiment via an annular axial outer gap 21 to the hot gas channel 8 and via an annular axial inner gap 23 to the cooling channel 14. Through the outer gap 21, the hot gas partial stream 16 enters the sealing space 20 and is swirled in this. For vortex guidance is simultaneously through the inner gap 23 into the sealing chamber 20, a partial cooling air flow 22nd injected, which lays on a hot gas partial flow vortex 25 in the sealing chamber 20 and exits into the hot gas channel 8.

Die Dichteinrichtung 18 hat einen gegenüber einer leitschaufelreihenseitigen vorderen Plattformringhinterkante 24 radial innen angeordneten Axialring 26, der stromabwärts in Richtung der Laufschaufelreihe 2 orientiert ist und einen radial nach außen gerichteten Endabschnitt 28 aufweist. Zudem hat die Dichteinrichtung 18 einen laufschaufelreihenseitigen vorderen Plattformringüberhang 30, der stromabwärts in Richtung der Leitschaufelreihe 1 orientiert ist und einen radial nach innen gerichteten Endabschnitt 32 aufweist. Die umlaufenden Endabschnitte 28, 32 weisen somit in entgegengesetzte radiale Richtungen, wobei sie einander zugewandt sind.The sealing device 18 has an opposite to a guide vane row-side front platform ring trailing edge 24 radially inwardly disposed axial ring 26 which is oriented downstream in the direction of the blade row 2 and has a radially outwardly directed end portion 28. In addition, the sealing device 18 has a blade row-side front platform ring overhang 30, which is oriented downstream in the direction of the guide blade row 1 and has a radially inwardly directed end portion 32. The circumferential end portions 28, 32 thus have in opposite radial directions, wherein they face each other.

Zur Bildung des Dichtraums 20 befinden sich der Axialring 26 und der Plattformringüberhang 30 in axialer Überlappung. Dabei befinden sie sich in dem in Figur 1 gezeigten Ausführungsbeispiel derart in axialer Überlappung, dass der Dichtraum 20 nicht über seine gesamte axiale Erstreckung zum Heißgaskanal 8 geöffnet ist, sondern lediglich im Bereich nahe der Plattformringhinterkante 24.To form the sealing space 20, the axial ring 26 and the platform ring overhang 30 are in axial overlap. They are in the in FIG. 1 shown embodiment in axial overlap that the sealing space 20 is not open over its entire axial extent to the hot gas channel 8, but only in the area near the platform ring trailing edge 24th

Der Axialring 26 erstreckt sich mit einem zylinderförmigen Ringabschnitt 34 in Axialrichtung der Strömungsmaschine und ist radial innen zum Plattformringüberhang 30 angeordnet. Sein Endabschnitt 28 erstreckt sich vom Ringabschnitt 34 und ist stromabwärts geneigt angestellt, wobei er sich radial nach außen erstreckt. Der Endabschnitt 28 weist somit in Richtung des vorderen Plattformringüberhangs 30.The axial ring 26 extends with a cylindrical annular portion 34 in the axial direction of the turbomachine and is arranged radially inward to the platform ring overhang 30. Its end portion 28 extends from the ring portion 34 and is made inclined downstream, extending radially outwardly. The end portion 28 thus points in the direction of the front platform ring overhang 30.

Der vordere Plattformringüberhang 30 folgt in dem gezeigten Ausführungsbeispiel mit einem Ringabschnitt 37 einem idealen Strömungsverlauf des Heißgases über den laufschaufelreihenseitigen Plattformring 12. Er geht hierzu zum einen stufenlos in die Plattform 12 über und hat zum einen in Strömungsrichtung betrachtet eine sich trichterförmig öffnende Kontur.The front platform ring overhang 30 follows in the embodiment shown with a ring portion 37 an ideal flow of the hot gas over the blade row side platform ring 12. He goes for this purpose on a stepless in the platform 12 and has viewed in the flow direction a funnel-shaped opening contour.

Der Endabschnitt 32 des vorderen Plattformringüberhangs 30 erstreckt sich vom Ringabschnitt 37. Er verläuft orthogonal zur Axialrichtung und somit orthogonal zum Ringabschnitt 34 des Axialrings 26, wobei er sich radial nach innen erstreckt. Der Endabschnitt 32 hat eine kürze radiale Erstreckung als der Endabschnitt 28 des Axialrings 26. In dem gezeigten Ausführungsbeispiel hat er eine derartige radiale Erstreckung, dass er auf bzw. in etwa auf der gleichen radialen Höhe wie der Endabschnitt 28 des Axialrings 26 endet. Stromabwärts bildet der Endabschnitt 32 des Plattformringüberhangs 30 zusammen mit dem Endabschnitt 28 des Axialrings 26 den Innenpalt 23, der hier in Figur 1 quasi ein Axialspalt ist. Aufgrund der Neigung des Endabschnitts 28 ist der Innenspalt 23 dabei gegenüber einer nicht geneigten Anstellung des Endabschnitts 28 axial erweitert. Stromaufwärts bildet der Endabschnitt 32 des vorderen Plattformringüberhangs 30 zusammen mit der leitschaufelseitigen Plattformringhinterkante 24 den Außenspalt 21.The end portion 32 of the front platform ring overhang 30 extends from the ring portion 37. It is orthogonal to the axial direction and thus orthogonal to the ring portion 34 of the axial ring 26, extending radially inwardly. The end portion 32 has a short Radial extent than the end portion 28 of the axial ring 26. In the illustrated embodiment, it has such a radial extent that it ends at or approximately at the same radial height as the end portion 28 of the axial ring 26. Downstream forms the end portion 32 of the platform ring overhang 30 together with the end portion 28 of the axial ring 26, the inner gap 23, the here in FIG. 1 almost an axial gap. Due to the inclination of the end portion 28 of the inner gap 23 is thereby axially expanded with respect to a non-inclined employment of the end portion 28. Upstream, the end portion 32 of the front platform ring overhang 30 forms the outer nip 21, together with the vane side platform ring trailing edge 24.

Bei dem in Figur 2 gezeigten Ausführungsbeispiel einer Dichteinrichtung 18 zwischen einer Leitschaufelreihe 1 und einer stromabwärtigen Laufschaufelreihe 2 einer Strömungsmaschine zum Verhindern eines Heißgaseinzugs 16 aus einem radial äußeren Heißgaskanal 8 in einen radial inneren Kühlkanal 14 unter Bildung eines Dichtraums 20 sind im wesentlichen Unterschied zum Ausführungsbeispiel nach Figur 1 beide Endabschnitte 28, 32 orthogonal zum axialen Ringabschnitt 34 bzw. zur Axialrichtung der Strömungsmaschine orientiert. Die Endabschnitte 28, 32 sind quasi parallel zueinander ausgerichtet. Allerdings sind sie in Radialrichtung der Strömungsmaschine derart voneinander beanstandet, dass ein ringartiger Innenspalt 23 zum Einblasen eines Kühlluftteilstroms 22 in den Dichtraum 20 eine größere axiale Komponente als radiale Komponente hat und somit quasi ein Radialspalt ist.At the in FIG. 2 shown embodiment of a sealing device 18 between a stator blade 1 and a downstream blade row 2 of a turbomachine to prevent a hot gas inlet 16 from a radially outer hot gas channel 8 in a radially inner cooling channel 14 to form a sealing space 20 are essentially different from the embodiment according to FIG. 1 both end portions 28, 32 oriented orthogonal to the axial ring portion 34 and to the axial direction of the turbomachine. The end sections 28, 32 are aligned almost parallel to one another. However, in the radial direction of the turbomachine, they are objected to one another in such a way that a ring-like inner gap 23 for injecting a cooling air partial flow 22 into the sealing space 20 has a greater axial component than a radial component and thus is virtually a radial gap.

Zudem sind im wesentlichen Unterschied die Endabschnitte 28, 32 derart von einer leitschaufelseitigen Plattformringhinterkante 24 beabstandet, dass sich ein ringartiger axialer Außenspalt 21 quasi über die gesamte axiale Erstreckung des Axialrings 26 erstreckt und der Dichtraum 20 somit quasi über seine gesamte axiale Erstreckung zum Heißgaskanal 8 geöffnet ist.In addition, the end sections 28, 32 are substantially different from a guide blade-side platform ring trailing edge 24 in that a ring-like axial outer gap 21 extends virtually over the entire axial extent of the axial ring 26 and the sealing space 20 thus opens to the hot gas channel 8 virtually over its entire axial extent is.

Wie in den Figuren 1 und 2 zu erkennen, ist eine jeweilige Leitschaufel 35 der Leitschaufelreihe 1 ohne einen hinteren Plattformüberhang ausgebildet. Die Leitschaufel 35 weist jeweils einen zu einer hinteren Plattformkante radial innen positionierten Axialvorsprung mit einem radial nach außen gerichteten Endbereich auf. Im zur Leitschaufelreihe 1 montierten Zustand bilden die nebeneinander liegenden Axialvorsprünge den Axialring 26, wobei die Endbereiche den umlaufenden Endabschnitt 28 bilden.As in the Figures 1 and 2 to recognize a respective vane 35 of the vane row 1 is formed without a rear platform overhang. The vane 35 has in each case one to a rear platform edge radially inwardly positioned axial projection with a radially outwardly directed end portion. In the state mounted to the guide vane row 1, the adjacent axial projections form the axial ring 26, wherein the end regions form the peripheral end section 28.

In Figur 3 ist eine erfindungsgemäße Laufschaufel 36 zur Bildung einer vorgenannten Laufschaufelreihe 2 gezeigt. Die Laufschaufel 36 hat hierzu in Strömungsrichtung eines Heißgases betrachtet einen vorderen Plattformüberhang 38 mit einem radial nach innen gerichteten Endbereich 40. Der vordere Plattformüberhang 38 folgt einem idealen Strömungsverlauf des Heißgases über eine Schaufelplattform 42. Der vordere Plattformüberhang 38 geht stufenlos in die Schaufelplattform 42 über und ist entsprechend der Schaufelplattform 42 in Strömungsrichtung aufsteigend schräg angestellt. Zudem weist die in Figur 3 gezeigte Laufschaufel 36 eine hintere Plattformüberhang 44 auf, der nahezu axial zur Axialrichtung ausgerichtet ist. Im zur Laufschaufelreihe 1 montierten Zustand bilden die nebeneinander liegenden vorderen Plattformüberhänge 38 den vorderen Plattformringüberhang 30, wobei die Endbereiche 40 den umlaufenden Endabschnitt 32 bilden.In FIG. 3 a blade 36 according to the invention for the formation of an aforementioned blade row 2 is shown. The blade 36 has seen in the direction of flow of a hot gas, a front platform overhang 38 with a radially inwardly directed end portion 40. The front platform overhang 38 follows an ideal flow of the hot gas through a paddle platform 42. The front platform overhang 38 is steplessly into the paddle platform 42 and is in accordance with the blade platform 42 ascending inclined in the flow direction. In addition, the in FIG. 3 shown blade 36 a rear platform overhang 44 which is aligned almost axially to the axial direction. In the assembled state of the blade row 1 state, the adjacent front platform overhangs 38 form the front platform ring overhang 30, wherein the end portions 40 form the peripheral end portion 32.

Offenbart ist eine Strömungsmaschine, mit einer Dichteinrichtung zum Verhindern eines Heißgaseinzugs durch einen Axialspalt zwischen einer Strömungsprofilreihe und einer Laufschaufelreihe aus einem Heißgaskanal in einen Kühlkanal, wobei die Dichteinrichtung einen stromabwärts orientierten leitschaufelseitigen Axialring hat, der sich axial über eine Plattformringhinterkante der Strömungsprofilreihe erstreckt und einen radial nach außen gerichteten Endabschnitt hat, und einen stromaufwärts gerichteten laufschaufelseitigen Plattformringüberhang aufweist, der einen radial nach innen gerichteten Endabschnitt aufweist, wobei der Axialring radial innen zum Plattformringüberhang angeordnet ist und mit diesem eine axiale Überlappung bildet, wobei der vordere Plattformringüberhang zumindest abschnittsweise einem idealen Strömungsverlauf des Heißgases über den laufschaufelreihenseitigen Plattformring folgt, sowie eine Leitschaufel und eine Laufschaufel.Disclosed is a turbomachine having sealing means for preventing hot gas ingress through an axial gap between a series of airfoils and a blade row from a hot gas passage into a cooling passage, the sealing means having a downstream orifice-side axial ring extending axially beyond a platform ring trailing edge of the airfoil row and a radial one has an outwardly directed end portion, and an upstream blade-side platform ring overhang having a radially inwardly directed end portion, wherein the Axialring is arranged radially inwardly to the platform ring overhang and forms an axial overlap therewith, wherein the front platform ring overhang at least partially an ideal flow of the Hot gas over the blade row side platform ring follows, as well as a vane and a blade.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Leitschaufelreihevane row
22
LaufschaufelreiheBlade row
44
Schaufelblattairfoil
66
Schaufelblattairfoil
88th
HeißgaskanalHot gas duct
1010
Plattformringplatform ring
1212
Plattformringplatform ring
1414
Kühlkanalcooling channel
1616
Heißgasteilstrom / HeißgaseinzugHot gas partial flow / hot gas intake
1818
Dichteinrichtungsealing device
2020
Dichtraumtight space
2121
Außenspaltouter gap
2222
KühlluftteilstromCooling air partial stream
2323
Innenspaltinterior gap
2424
PlattformringhinterkantePlatform ring trailing edge
2525
HeißgasteilstromwirbelHot gas partial flow vortices
2626
Axialringaxial ring
2828
Endabschnittend
3030
PlattformringüberhangPlatform ring overhang
3232
Endabschnittend
3434
Ringabschnittring section
3535
Leitschaufelvane
3636
Laufschaufelblade
3737
Ringabschnittring section
3838
PlattformüberhangDeck overhang
4040
Endbereichend
4242
Schaufelplattformblade platform
4444
vorderer Plattformüberhangfront platform overhang

Claims (8)

Strömungsmaschine, mit einer feststehenden Strömungsprofilreihe (1) und einer stromabwärtigen Laufschaufelreihe (2), zwischen denen ein radial innerer Kühlkanal (14) gebildet ist, wobei die Strömungsprofilreihe (1) und die Laufschaufelreihe (2) jeweils einen Plattformring (10, 12) aufweisen, der einen radial äußeren Heißgaskanal (8) begrenzt, und mit einer Dichteinrichtung (18) zum Verhindern eines Heißgaseinzugs (16) durch einen Axialspalt zwischen den Reihen (1, 2) aus dem Heißgaskanal (8) in den Kühlkanal (14), dadurch gekennzeichnet, dass die Dichteinrichtung (18) einen stromabwärts orientierten leitschaufelseitigen Axialring (26) hat, der sich axial über eine Plattformringhinterkante (24) der Strömungsprofilreihe (1) erstreckt und einen radial nach außen gerichteten Endabschnitt (28) hat, und dass die Dichteinrichtung (18) einen stromaufwärts gerichteten laufschaufelseitigen Plattformringüberhang (30) aufweist, der einen radial nach innen gerichteten Endabschnitt (32) aufweist, wobei der Axialring (26) radial innen zum Plattformringüberhang (30) angeordnet ist und mit diesem eine axiale Überlappung bildet, wobei der vordere Plattformringüberhang (30) zumindest abschnittsweise einem idealen Strömungsverlauf des Heißgases über den laufschaufelreihenseitigen Plattformring (12) folgt.Turbomachine having a fixed airfoil row (1) and a downstream blade row (2), between which a radially inner cooling channel (14) is formed, wherein the airfoil row (1) and the blade row (2) each have a platform ring (10, 12) defining a radially outer hot gas duct (8), and with a sealing means (18) for preventing a hot-gas feeder (16) by an axial gap between the rows (1, 2) from the hot-gas duct (8) into the cooling passage (14), characterized characterized in that the sealing device (18) has a downstream-oriented vane-side axial ring (26) which extends axially beyond a platform ring trailing edge (24) of the airfoil row (1) and has a radially outwardly directed end portion (28), and in that the sealing device ( 18) has an upstream blade-side platform ring overhang (30) having a radially inwardly directed end portion (32), wherein the axial ring (26) is disposed radially inward of the platform ring overhang (30) and forms an axial overlap therewith, wherein the front platform ring overhang (30) at least partially follows an ideal flow pattern of the hot gas over the blade row side platform ring (12) , Strömungsmaschine nach Anspruch 1, wobei die Endabschnitte (28, 30) in radialer Richtung voneinander beabstandet sind.Turbomachine according to claim 1, wherein the end portions (28, 30) are spaced apart in the radial direction. Strömungsmaschine nach Anspruch 1, wobei die Endabschnitte (28, 30) auf gleicher radialer Höhe enden.Turbomachine according to claim 1, wherein the end portions (28, 30) terminate at the same radial height. Strömungsmaschine nach einem der vorhergehenden Ansprüche, wobei der Endabschnitt (28) des Axialrings (26) eine größere radiale Erstreckung als der Endabschnitt (32) des vorderen Plattformringüberhangs (30) hat.Turbomachine according to one of the preceding claims, wherein the end portion (28) of the axial ring (26) has a greater radial extent than the end portion (32) of the front platform ring overhang (30). Strömungsmaschine nach einem der Ansprüche 1 bis 4, wobei die Endabschnitte (28, 30) parallel und in radialer Richtung versetzt zueinander verlaufen.Turbomachine according to one of claims 1 to 4, wherein the end portions (28, 30) parallel to and in the radial direction offset from each other. Strömungsmaschine nach einem der Ansprüche 1 bis 4, wobei die Endabschnitte (28, 30) zueinander angestellt sind.Turbomachine according to one of claims 1 to 4, wherein the end portions (28, 30) are set to each other. Leitschaufel (35) für eine Strömungsmaschine nach einem der Ansprüche 1 bis 6.Guide vane (35) for a turbomachine according to one of claims 1 to 6. Laufschaufel (36) für eine Strömungsmaschine nach einem der Ansprüche 1 bis 6.Blade (36) for a turbomachine according to one of claims 1 to 6.
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Cited By (1)

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CN111287803A (en) * 2018-12-07 2020-06-16 安萨尔多能源公司 Stator assembly for a gas turbine and gas turbine comprising said stator assembly

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US20100172749A1 (en) 2007-03-29 2010-07-08 Mitsuhashi Katsunori Wall of turbo machine and turbo machine
US20100183426A1 (en) * 2009-01-19 2010-07-22 George Liang Fluidic rim seal system for turbine engines
US8075256B2 (en) 2008-09-25 2011-12-13 Siemens Energy, Inc. Ingestion resistant seal assembly
EP2573329A2 (en) 2011-09-22 2013-03-27 Pratt & Whitney Canada Corp. Air system architecture for a mid-turbine frame module

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EP1380726A2 (en) * 2002-07-10 2004-01-14 Mitsubishi Heavy Industries, Ltd. Stationary blade in gas turbine and gas turbine comprising the same
US7540709B1 (en) 2005-10-20 2009-06-02 Florida Turbine Technologies, Inc. Box rim cavity for a gas turbine engine
US20100172749A1 (en) 2007-03-29 2010-07-08 Mitsuhashi Katsunori Wall of turbo machine and turbo machine
US8075256B2 (en) 2008-09-25 2011-12-13 Siemens Energy, Inc. Ingestion resistant seal assembly
US20100183426A1 (en) * 2009-01-19 2010-07-22 George Liang Fluidic rim seal system for turbine engines
EP2573329A2 (en) 2011-09-22 2013-03-27 Pratt & Whitney Canada Corp. Air system architecture for a mid-turbine frame module

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111287803A (en) * 2018-12-07 2020-06-16 安萨尔多能源公司 Stator assembly for a gas turbine and gas turbine comprising said stator assembly
CN111287803B (en) * 2018-12-07 2023-07-14 安萨尔多能源公司 Stator assembly for a gas turbine and gas turbine comprising said stator assembly

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