CH408960A - Radial seal for turbine runners - Google Patents

Radial seal for turbine runners

Info

Publication number
CH408960A
CH408960A CH900762A CH900762A CH408960A CH 408960 A CH408960 A CH 408960A CH 900762 A CH900762 A CH 900762A CH 900762 A CH900762 A CH 900762A CH 408960 A CH408960 A CH 408960A
Authority
CH
Switzerland
Prior art keywords
turbine
sealing ring
segments
radial seal
sealing
Prior art date
Application number
CH900762A
Other languages
German (de)
Inventor
Hermann Dipl Ing Breidert
Veenhoff Ferdinand
Original Assignee
Licentia Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Licentia Gmbh filed Critical Licentia Gmbh
Publication of CH408960A publication Critical patent/CH408960A/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/441—Free-space packings with floating ring
    • F16J15/442—Free-space packings with floating ring segmented
    • 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
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B19/00—Engines characterised by precombustion chambers
    • F02B19/14—Engines characterised by precombustion chambers with compression ignition
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

  

      Radialdichtung        für        Turbinenlaufräder       Die Erfindung betrifft eine     Radialdichtung    für       Turbinenlaufräder,    deren Schaufeln mit Spitzenban  dagen versehen sind.  



  Bei Turbinenlaufrädern, deren     Schaufeln    mit  einer Spitzenbandage versehen sind, sollen     Arbeits-          mittelverluste    dadurch     vermieden    werden, dass     die     Spitzen auf dem Deckband mit dem     Turbinengehäuse          bzw.    mit     einem    im Turbinengehäuse angeordneten  Dichtring eine     Radialdichtung    bilden. Solche Dich  tungen sind an sich bekannt.

   Der Nachteil dieser       Radialdichtungen    ist darin zu sehen, dass bei einem  betriebsbedingten Anstreifen der     Deckbandspitzen     am feststehenden Dichtring durch     örtliche    Tempera  turfelder ein Verziehen des Dichtringes eintreten  kann, wodurch die Dichtwirkung herabgesetzt wird.  Andererseits werden beim Anstreifen auch die Spit  zen auf dem Deckband     abgeschliffen,    so dass da  durch ebenfalls die Dichtwirkung beeinträchtigt ist.  Diesen Nachteil will die Erfindung beheben.  



  Die Erfindung besteht darin, dass ein aus radial  beweglichen Segmenten aufgebauter     Dichtring    mit  den Spitzen des     Schaufeldeckbandes    einen Dichtspalt  bildet. Die Segmente des Dichtringes können durch  Auflageflächen an den zwischen den Turbinenlaufrä  dern im Turbinengehäuse angeordneten     Leitschaufel-          trägem        zentriert    werden. Weiterhin können die Seg  mente des Dichtringes durch Federn gehalten werden,  die einerseits im Segment und andererseits in dem die  Turbinenlaufräder umgebenden Gehäuse verhakt  sind.  



  Der     Vorteil    der Erfindung ist, dass durch die  radiale Beweglichkeit der     Dichtringsegmente    die  beim möglichen     Anstreifen    der     Deckbandspitzen    an  den Dichtringen auftretenden Schäden vermieden  werden.  



  In der Zeichnung ist in den     Fig.    1 und 2 ein Aus-         führungsbeispiel    nach der Erfindung wiedergegeben.  In     Fig.    3 ist ein Beispiel für eine     Radialdichtung    an  einer     End-    oder Entnahmestufe gezeigt, bei der be  züglich der     Aufnahme    des federnden aus Segmenten  gebildeten Dichtringes     eine    andere Form     gewählt     wurde.  



  Die Turbinenlaufräder 20 und 21 sind mit Deck  bändern 13 versehen, auf denen Dichtungsspitzen 12       angeordnet    sind. Diese Dichtungsspitzen bilden mit  dem gemäss der     Erfindung    aus Segmenten 11 bzw.  19 aufgebauten Dichtring den Dichtungsspalt 14. Die  Segmente 11 werden durch die Auflageflächen 15 an  den im Gehäuse 18     gelagerten        Leitschaufeldeckeln     16 gegenüber dem     Turbinenlaufrad    20     zentriert    und  jeweils durch eine im Gehäuse und im Segment ver  hakte Feder 17 fixiert und gegen Verdrehung gesi  chert.  



  Bei der     Ausbildung    des Dichtungsringes     für    eine  Endstufe werden die Segmente 19 im     Leitschaufel-          deckel    16 aufgenommen, wobei die Segmente in Art  von Federzungen ausgebildet sind und     somit    eine  radiale     Beweglichkeit    sichern.



      Radial seal for turbine wheels The invention relates to a radial seal for turbine wheels, the blades of which are provided with Spitzenban dagen.



  In the case of turbine runners, the blades of which are provided with a tip bandage, the loss of working medium should be avoided by the tips on the shroud forming a radial seal with the turbine housing or with a sealing ring arranged in the turbine housing. Such seals are known per se.

   The disadvantage of these radial seals is that if the shroud tips rub against the stationary sealing ring due to local temperature fields, the sealing ring can warp, which reduces the sealing effect. On the other hand, the tips on the shroud are abraded when rubbed, so that the sealing effect is also impaired. The invention aims to remedy this disadvantage.



  The invention consists in that a sealing ring made up of radially movable segments forms a sealing gap with the tips of the blade shroud. The segments of the sealing ring can be centered by contact surfaces on the guide vane carriers arranged between the turbine runners in the turbine housing. Furthermore, the Seg ments of the sealing ring can be held by springs that are hooked on the one hand in the segment and on the other hand in the housing surrounding the turbine wheels.



  The advantage of the invention is that the radial mobility of the sealing ring segments avoids the damage that occurs when the shroud tips rub against the sealing rings.



  In the drawing, an embodiment according to the invention is shown in FIGS. 1 and 2. In Fig. 3 an example of a radial seal at an end or removal stage is shown in which be with respect to the inclusion of the resilient sealing ring formed from segments another shape was selected.



  The turbine runners 20 and 21 are provided with shrouds 13 on which sealing tips 12 are arranged. These sealing tips form the sealing gap 14 with the sealing ring constructed from segments 11 and 19 according to the invention. The segments 11 are centered by the bearing surfaces 15 on the guide vane covers 16 mounted in the housing 18 with respect to the turbine impeller 20 and each by one in the housing and one in the segment ver hooked spring 17 fixed and secured against rotation.



  When the sealing ring is designed for an output stage, the segments 19 are received in the guide vane cover 16, the segments being designed in the form of spring tongues and thus ensuring radial mobility.

Claims (1)

PATENTANSPRUCH Radialdichtung für Turbinenlaufräder, deren Schaufeln mit Spitzenbandagen versehen sind, da durch gekennzeichnet, dass ein aus radial bewegli chen Segmenten (11) aufgebauter Dichtring mit den Spitzen (12) des Schaufeldeckbandes (13) einen Dichtspalt bildet. UNTERANSPRÜCHE 1. PATENT CLAIM Radial seal for turbine runners, the blades of which are provided with point bandages, characterized in that a sealing ring made up of radially movable segments (11) forms a sealing gap with the tips (12) of the blade shroud (13). SUBCLAIMS 1. Dichtung nach Patentanspruch, dadurch ge- kennzeichnet, dass die Segmente (11) des Dichtringes durch Auflageflächen (15) an den zwischen den Tur- binenlaufrädern im Turbinengehäuse (18) angeordne ten Leitschaufelträgern (16) zentriert sind. 2. Dichtung nach Patentanspruch und Unteran- spruch 1, dadurch gekennzeichnet, dass die Segmente (11) des Dichtringes durch Federn (17) gehalten wer den, die einerseits im Segment und andererseits in dem die Turbinenlaufräder umgebenden Gehäuse (18) verhakt sind. Seal according to patent claim, characterized in that the segments (11) of the sealing ring are centered by contact surfaces (15) on the guide vane carriers (16) arranged between the turbine wheels in the turbine housing (18). 2. Seal according to claim and dependent claim 1, characterized in that the segments (11) of the sealing ring held by springs (17) who are hooked on the one hand in the segment and on the other hand in the housing (18) surrounding the turbine runners.
CH900762A 1961-09-04 1962-07-25 Radial seal for turbine runners CH408960A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEL0039928 1961-09-04

Publications (1)

Publication Number Publication Date
CH408960A true CH408960A (en) 1966-03-15

Family

ID=7268860

Family Applications (1)

Application Number Title Priority Date Filing Date
CH900762A CH408960A (en) 1961-09-04 1962-07-25 Radial seal for turbine runners

Country Status (3)

Country Link
BE (1) BE621436A (en)
CH (1) CH408960A (en)
NL (1) NL282822A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2445705A1 (en) * 1973-09-27 1975-04-10 Gen Electric SHELL ARRANGEMENT
EP0018627A1 (en) * 1979-05-08 1980-11-12 Nissan Motor Co., Ltd. Improved labyrinth seal construction
EP0132182A1 (en) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine blade tip seal
FR2577281A1 (en) * 1985-02-13 1986-08-14 Snecma TURBOMACHINE CASING ASSOCIATED WITH A DEVICE FOR ADJUSTING THE GAME BETWEEN MOBILE AUBES AND CARTER
EP1008725A3 (en) * 1998-12-07 2003-12-03 General Electric Company Compressor interstage seal

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH482915A (en) * 1967-11-03 1969-12-15 Sulzer Ag Guide device for axial turbine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2445705A1 (en) * 1973-09-27 1975-04-10 Gen Electric SHELL ARRANGEMENT
EP0018627A1 (en) * 1979-05-08 1980-11-12 Nissan Motor Co., Ltd. Improved labyrinth seal construction
EP0132182A1 (en) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine blade tip seal
FR2577281A1 (en) * 1985-02-13 1986-08-14 Snecma TURBOMACHINE CASING ASSOCIATED WITH A DEVICE FOR ADJUSTING THE GAME BETWEEN MOBILE AUBES AND CARTER
EP0192556A1 (en) * 1985-02-13 1986-08-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine cylinder with a device to adjust the tip clearance between the turbine blades and the cylinder
US4787817A (en) * 1985-02-13 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Device for monitoring clearance between rotor blades and a housing
EP1008725A3 (en) * 1998-12-07 2003-12-03 General Electric Company Compressor interstage seal

Also Published As

Publication number Publication date
BE621436A (en) 1962-08-16
NL282822A (en)

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