EP2808492B1 - Palier de turbine doté d'un système de purge et procédé de purge d'un flux de gaz d'arrêt - Google Patents

Palier de turbine doté d'un système de purge et procédé de purge d'un flux de gaz d'arrêt Download PDF

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Publication number
EP2808492B1
EP2808492B1 EP14168204.7A EP14168204A EP2808492B1 EP 2808492 B1 EP2808492 B1 EP 2808492B1 EP 14168204 A EP14168204 A EP 14168204A EP 2808492 B1 EP2808492 B1 EP 2808492B1
Authority
EP
European Patent Office
Prior art keywords
sealing
turbine stage
rotor element
gas
stage according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP14168204.7A
Other languages
German (de)
English (en)
Other versions
EP2808492A1 (fr
Inventor
Alexander Böck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP2808492A1 publication Critical patent/EP2808492A1/fr
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Not-in-force legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the present invention relates to a turbine stage of a gas turbine with a Ausblasanord- tion for blowing a barrier gas flow into a cavity according to the preamble of claim 1, as for example from DE 699 26 574 T2 , from the DE 693 05 326 T2 and the DE 693 27 180 T2 is known, a method for operating such a turbine stage and a gas turbine with such a turbine stage.
  • a turbine stage has a gas channel, in which a plurality of guide and play grids are usually arranged in order to convert energy of a gas gas flowing through the gas channel into torques of a rotor of the gas turbine.
  • Cavities for example radial recesses in the rotor, in which radially inner blade tips or inner shrouds of guide grids intervene communicate with the gas channel.
  • these can be limited by one or more seals.
  • a seal can delimit an upstream against a downstream cavity in order to avoid an undesirable underflow of a guide grid.
  • An object of an embodiment of the present invention is to improve operation of a gas turbine.
  • a turbine stage has a gas channel, in which one or more playpens are arranged and in the operation of a working gas, in particular an exhaust gas from an upstream combustion chamber, flows through.
  • a guide grid may be arranged before and / or after at least one playpens.
  • the running channel can diverge in the direction of flow, at least in sections.
  • At least one cavity which is delimited by an end face of a one-part or multi-part rotor element and by a rotor element-proof seal, communicates with the gas channel.
  • the rotor element may comprise a blade assembly having one or more blades of a turbine stage runner which may be detachably or fixedly connected, in particular integrally, to a rotor of the turbine stage.
  • the end face limits the cavity axially or forms an end wall, in particular downstream, of the cavity.
  • the seal likewise axially delimits the cavity or forms an end wall, in particular upstream, of the cavity.
  • the cavity may be limited in one embodiment by a further rotorelementfeste seal through which the cavity communicates with the gas channel, in particular a labyrinth seal with one or more axial flanges, which may face one or more fixed axial flanges of the turbine stage.
  • Radially inside the cavity may be limited in one embodiment by an axial projection of the rotor element end face, in particular a seal carrier on which the rotorelementfeste seal is arranged.
  • the cavity may be a chamber between a blade disk and an inner shroud of a, in particular upstream, guide rail.
  • the rotor element-proof seal can in particular be a labyrinth seal with one or more radial sealing flanges, in particular radial sealing tips, be radially opposite to the counter-seal, in particular a honeycomb seal.
  • the rotor element-tight seal may limit the cavity to a further, upstream cavity.
  • the turbine stage has a blow-out arrangement with one or more, over the circumference, preferably equidistantly, distributed gas passages for blowing a sealing gas flow, in particular a blocking air flow, in the cavity.
  • one or more, preferably all gas passages of the blow-out arrangement are formed for blowing out the barrier gas flow with a swirl in the circumferential direction, which in one embodiment is in the same direction with a rotational direction of the turbine stage.
  • a circumferential spin-flow blocking flow can be injected, so that a shear flow due to the peripheral speed of the rotor can be reduced or avoided and thus in particular an efficiency and thus the operation of the turbine stage can be improved.
  • a leakage flow into the cavity can occur via the rotor element-fixed seal. This may be desirable, in particular in order to cool the rotor element, in particular its end face, by the leakage flow. However, if the preferably drainage-free leakage flow strikes directly on the swirling purging gas flow, mixing thereof can reduce the circumferential swirl of the purging gas flow.
  • an outlet opening of one or more, preferably all gas passages of the blow-out arrangement is offset radially outward from the rotor element-fixed seal.
  • the sealing gas flow is, so to speak through the blow-out radially guided by a leakage flow over the rotorelementfeste seal away and only radially outwardly blown with swirl, so that a disturbance by the leakage flow is reduced, in particular at least substantially prevented.
  • the purge gas flow is accordingly blown out through the exhaust assembly with a swirl in the circumferential direction radially outward of the rotor element fixed seal in this cavity.
  • a gas passage may be curved in the circumferential direction.
  • one or more deflecting elements or surfaces can be arranged in a gas passage in order to impose a velocity component in the circumferential direction on the sealing gas flow flowing through them.
  • a gas passage is formed as a through bore or through opening or passage of a pipe.
  • the tube can be manufactured as a separate component and attached to the rotor element, in particular a rotorelementfesten seal carrier on which the rotorelementfeste seal is arranged, releasably or permanently, in particular material, frictionally or positively fastened, in particular welded, glued, -solders, -latches , -schraubt or plugged.
  • a pipe can also be formed integrally with the rotor element, in particular by a pipe jacket being excavated around a through-hole, in particular free-milled.
  • the tube may in one embodiment, at least substantially, extend along its length, or in at least a portion, preferably at least in an exit opening quarter of its length, at least substantially in a plane perpendicular to a rotational axis of the turbine stage.
  • the sealing gas flow can be performed in a design on a short path through the leakage flow.
  • the tube may be inclined at least in sections, preferably at least in an opening opening next quarter of its length, against the axis of rotation of the turbine stage, in particular in order to displace an entry opening axially.
  • one or more, preferably all gas passages of the blow-out arrangement have an inlet opening which communicates with a pressure reservoir, in particular a barrier air reservoir.
  • a bypass passage between the pressure reservoir and the cavity is fluidly connected in parallel to the exhaust arrangement.
  • the bypass passage can be defined in particular by the rotor element-fixed seal, preferably a sealing gap between it and an opposing counter-seal, in particular an inlet lining, preferably a guide grid.
  • a pressurized gas in particular air, preferably from a compressor upstream of the turbine stage, led into an upstream further cavity and there in a, preferably larger, leakage flow through the rotorelementfeste seal, in particular for cooling the rotor element, and a, preferably smaller, barrier gas flow to be divided.
  • the turbine stage may include an upstream additional cavity that communicates with a pressure reservoir, a seal gap over the rotor member fixed seal, and the blowout assembly.
  • a turbine stage according to the invention can be used in particular in a gas turbine, preferably an aircraft engine.
  • Fig. 1 shows a part of a turbine stage according to an embodiment of the present invention in a meridian section with a gas channel 11, in which a plurality of playpens are arranged, of which Fig. 1 two blades 1 are partially visible. Between these a guide grid is arranged, of which in Fig. 1 a vane 2 is partially visible.
  • the front side forms a downstream end wall of the cavity 9 (right in Fig. 1 ).
  • the seal 3A, 3B also limits the cavity 9 axially (to the left in FIG Fig. 1 ).
  • the cavity 9 is delimited by a further rotor element-fixed labyrinth seal 5, through which the cavity communicates with the gas channel 11.
  • a seal carrier 3 on which the rotorelementfeste seal 3A, 3B is arranged.
  • the cavity thus forms a chamber between the blade disc and an inner shroud of the upstream Leitgitters with the guide vanes 2.
  • the guide grid has a radially inner counter-seal in the form of an inlet lining 4, the rotorelementfesten seal 3A, 3B opposite and defines with this a sealing gap, the parallel to a rotational axis of the turbine stage (horizontally in Fig. 1 ).
  • the rotorelementfeste seal is a labyrinth seal with two radial sealing tips 3A, 3B, which are radially opposite the inlet lining in the form of a honeycomb seal 4.
  • the rotorelementfeste seal 3A, 3B limits the cavity 9 against a further, upstream cavity 10, which by the way by a labyrinth seal 6 and a downstream end face of the in Fig. 1 left Laufgitters, the seal carrier 3 and the connecting flange to this in Fig. 1 left playpen is limited and also communicates with a pressure reservoir 12 and the labyrinth seal 6 with the gas channel 11.
  • the turbine stage has a blow-out arrangement with a plurality of gas passages distributed equidistantly over the circumference for blowing out a blocking air flow into the cavity 9.
  • the gas passages are formed as a through-hole of pipes, of which in Fig. 1 a tube 7 is shown.
  • the tube 7 is in the execution of Fig. 1 manufactured as a separate component and on the rotorelementfesten seal carrier 3, on which the rotorelementfeste seal 3A, 3B is arranged, releasably or permanently, in particular material, friction or positively secured, in particular welded, glued, -slöt-, snaps, -schraubt or plugged in.
  • the tube may also be integrally formed with the seal carrier by a tube jacket exposed to a through hole, in particular free-milled.
  • the tubes 7 and thus also their through holes or gas passages are in the circumferential direction (from the plane of the Fig. 1 out) to blow a purge gas flow having a swirl in the circumferential direction, which is in the same direction as a rotational direction of the turbine stage.
  • a circumferential spin-loaded blocking flow can be injected, so that a shear flow due to the peripheral speed reduced or avoided the rotor and thus in particular an efficiency and thus the operation of the turbine stage is improved.
  • a leakage flow enters the cavity 9 via the rotor element-fixed seal 3A, 3B. This is desirable to cool the face of the blade disk and / or the disk-blade connection by the leakage flow.
  • Outlet openings 8 of the tubes 7 and their gas passages are of the rotorelementfesten seal 3A, 3B radially outward (vertically upward in Fig. 1 ).
  • the sealing gas flow is guided, so to speak through the blow-out radially through a leakage flow over the rotorelementfeste seal away and only radially outwardly blown out with swirl, so that a disturbance by the leakage flow is reduced, preferably prevented.
  • the tubes 7 extend in the execution of Fig. 1 over its entire length in a plane perpendicular to a rotational axis of the turbine stage (vertical plane to the plane of the drawing) Fig. 1 ).
  • the sealing gas flow can be performed in a design on a short path through the leakage flow.
  • the tubes 7 extend in an exit opening next half 7A of their length (shown at the top in FIG Fig. 2 ) Also in the plane perpendicular to the axis of rotation. In a next opening half 7B of their length (bottom in Fig. 2 ), however, they are inclined by approximately 45 ° to the axis of rotation of the turbine stage, in particular, to move their inlet openings axially upstream.
  • a bypass passage is defined by a sealing gap between the rotorelementfesten seal 3A, 3B and the opposite inlet lining 4 of the guide grid and fluidly connected in parallel to the blow-out.
  • a compressed gas in particular air, preferably from a compressor upstream of the turbine stage, guided into the further upstream cavity 10 and there divided into a, preferably larger, leakage current via the rotorelementfeste seal 3A, 3B for cooling the rotor element and a, preferably smaller, barrier gas flow through the blowout.
  • the gas passages of the blow-out arrangement each have an inlet opening which communicates with the pressure reservoir 12 via the further upstream cavity 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Claims (12)

  1. Palier de turbine doté d'une conduite de gaz (11), dans laquelle au moins une grille d'écoulement (1) est agencée, une cavité (9) en communication avec la conduite de gaz et délimitée par un côté frontal d'un élément de rotor et par un joint monté sur l'élément de rotor (3A, 3B), et un procédé de purge (7) comportant au moins un passage de gaz constitué d'un passage foré d'un tuyau (7), pour la purge d'un flux de gaz d'arrêt dans cette cavité, le passage de gaz étant agencé pour la purge d'un flux de gaz d'arrêt par une torsion dans la direction de circonférence et présentant un orifice de sortie (8), qui est déporté radialement vers l'extérieur par le joint monté sur l'élément de rotor, caractérisé par un support de joint monté sur l'élément de rotor (3) sur lequel le joint et le tuyau sont agencés.
  2. Palier de turbine selon la revendication précédente, caractérisé en ce que le passage de gaz est courbé en direction de circonférence.
  3. Palier de turbine selon l'une des revendications précédentes, caractérisé en ce que le tuyau (7) est fixé à l'élément de rotor ou intégralement formé avec l'élément de rotor.
  4. Palier de turbine selon la revendication précédente, caractérisé en ce que le tuyau s'étend, au moins par section et préférablement au moins sur un quart de sa longueur (7A) proche de l'orifice de sortie, au moins substantiellement sur un niveau qui est perpendiculaire à un axe de rotation du palier de turbine.
  5. Palier de turbine selon l'une des revendications précédentes, caractérisé en ce que le passage de gaz présente un orifice d'entrée communicant avec un réservoir de pression (12).
  6. Palier de turbine selon la revendication précédente, caractérisé par un passage de dérivation fluidiquement parallèle au système de purge entre le réservoir de pression et la cavité.
  7. Palier de turbine selon l'une des revendications précédentes, caractérisé en ce que la cavité est limitée radialement et extérieurement par un autre joint (5) monté sur l'élément de rotor.
  8. Palier de turbine selon l'une des revendications précédentes, caractérisé en ce que le joint monté sur l'élément de rotor est un joint à labyrinthe comportant au moins une bride d'étanchéité radiale (3A, 3B).
  9. Palier de turbine selon l'une des revendications précédentes, caractérisé en ce que l'élément de rotor présente un agencement d'aube mobile comportant au moins une aube mobile (1).
  10. Palier de turbine selon l'une des revendications précédentes, caractérisé par une grille de guidage (2) avec un contre-joint interne radial (4) opposé au joint monté sur l'élément de rotor et définissant un jeu d'étanchéité avec celui-ci.
  11. Turbine à gaz, notamment réacteur d'avion, comportant au moins un palier de turbine selon l'une des revendications précédentes.
  12. Procédé d'exploitation d'un palier de turbine selon l'une des revendications 1 à 10, le flux de gaz d'arrêt étant purgé dans la cavité (9) par le joint monté sur l'élément de rotor (3A, 3B) via un procédé de purge (7) comportant une torsion dans la direction de circonférence radiale extérieure.
EP14168204.7A 2013-05-27 2014-05-14 Palier de turbine doté d'un système de purge et procédé de purge d'un flux de gaz d'arrêt Not-in-force EP2808492B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013209746.8A DE102013209746B4 (de) 2013-05-27 2013-05-27 Turbinenstufe mit einer Ausblasanordnung und Verfahren zum Ausblasen einer Sperrgasströmung

Publications (2)

Publication Number Publication Date
EP2808492A1 EP2808492A1 (fr) 2014-12-03
EP2808492B1 true EP2808492B1 (fr) 2016-11-02

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EP14168204.7A Not-in-force EP2808492B1 (fr) 2013-05-27 2014-05-14 Palier de turbine doté d'un système de purge et procédé de purge d'un flux de gaz d'arrêt

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US (1) US9644488B2 (fr)
EP (1) EP2808492B1 (fr)
DE (1) DE102013209746B4 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10316681B2 (en) * 2016-05-31 2019-06-11 General Electric Company System and method for domestic bleed circuit seals within a turbine
DE102016222608A1 (de) * 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
US10767485B2 (en) * 2018-01-08 2020-09-08 Raytheon Technologies Corporation Radial cooling system for gas turbine engine compressors
DE102018201295A1 (de) * 2018-01-29 2019-08-01 MTU Aero Engines AG Modul für eine strömungsmaschine
FR3128243B1 (fr) * 2021-10-14 2025-01-31 Safran Aircraft Engines Distributeur de turbine comportant un élément annulaire d’étanchéité

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
DE69305326T2 (de) * 1992-02-10 1997-05-07 United Technologies Corp Ejektor für kühlfluid
US5217348A (en) * 1992-09-24 1993-06-08 United Technologies Corporation Turbine vane assembly with integrally cast cooling fluid nozzle
US6065928A (en) * 1998-07-22 2000-05-23 General Electric Company Turbine nozzle having purge air circuit
DE10318852A1 (de) * 2003-04-25 2004-11-11 Rolls-Royce Deutschland Ltd & Co Kg Hauptgaskanal-Innendichtung einer Hochdruckturbine
US8277177B2 (en) * 2009-01-19 2012-10-02 Siemens Energy, Inc. Fluidic rim seal system for turbine engines
GB2477736B (en) * 2010-02-10 2014-04-09 Rolls Royce Plc A seal arrangement

Non-Patent Citations (1)

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Title
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Also Published As

Publication number Publication date
US9644488B2 (en) 2017-05-09
US20140348633A1 (en) 2014-11-27
DE102013209746B4 (de) 2014-12-18
DE102013209746A1 (de) 2014-11-27
EP2808492A1 (fr) 2014-12-03

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