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EP0192516B1 - Anstreifring für eine Gasturbine - Google Patents

Anstreifring für eine Gasturbine Download PDF

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Publication number
EP0192516B1
EP0192516B1 EP86400133A EP86400133A EP0192516B1 EP 0192516 B1 EP0192516 B1 EP 0192516B1 EP 86400133 A EP86400133 A EP 86400133A EP 86400133 A EP86400133 A EP 86400133A EP 0192516 B1 EP0192516 B1 EP 0192516B1
Authority
EP
European Patent Office
Prior art keywords
segments
turbine
grooves
support lugs
sectors
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.)
Expired
Application number
EP86400133A
Other languages
English (en)
French (fr)
Other versions
EP0192516A1 (de
Inventor
Jean-François Robert Imbault
Rolant René Mestre
Carmen Miraucourt
Rémy Paul Charles Ritt
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0192516A1 publication Critical patent/EP0192516A1/de
Application granted granted Critical
Publication of EP0192516B1 publication Critical patent/EP0192516B1/de
Expired 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the latter is made of a metallic material, so that when the wear material is a ceramic material, due to the large difference between the coefficients of expansion of metallic materials and ceramic materials the ring made of ceramic material must be formed from sectors independent of each other and coupled by their respective ends in order to allow the radius of the ring to follow the variations in the radius of the annular support as a function of the different temperatures that the latter takes for the different regimes of the turbine. This prevents the ring from being subjected to stresses incompatible with the mechanical resistance of the ceramic material which constitutes it.
  • the seal between contiguous sectors can be ensured by tongues engaged axially in first grooves made at the same radial level on the sides opposite said contiguous sectors.
  • the present invention relates to a turbine ring of this kind, but more specifically aims at an improved attachment method of the sectors on the annular support in order to minimize the thermal tensile stresses therein which ceramic materials have difficulty in cash out.
  • each sector has a median recess formed from the radially outer face of the sector two second axial grooves, circumferentially spaced, opening facing the side faces of the recess and in said second grooves engage the support fingers integral with a ferrule connected to the turbine casing and ensuring the attachment of the sectors one after the other all around the turbine, these attachment support fingers being housed in the grooves sheltered from the reintroduction of hot gases.
  • sealing between contiguous sectors can be advantageously ensured by tongues engaged axially in suitable grooves made at the same radial level on the flanks facing said contiguous sectors, as described in French patent 2,540,938 above- mentionned.
  • the ferrule has orifices through which pass jets of cooling air, these orifices being inclined so as to direct the jets on said support fingers.
  • springs arranged between the sectors and a cylindrical outer shell element ensure positive contact between finger-supports and axial grooves.
  • the pressure of these springs contributes to the damping of vibrations of which the sectors could be the object.
  • the annular space located beyond the sectors in the radial direction is subdivided into two cavities serving one for the cooling of the sectors and the other for controlling the expansions of the stator and by Consequently, the resulting play between the rotor and the turbine stator, these two cavities being separated by a sheet, the support of which on the radially external face of the sectors and the sealing are provided by said springs.
  • the insulation of the turbine casing from hot gases is also thus improved.
  • the present invention allows its use, thereby obtaining the advantages which result therefrom: thermal protection of the stator, reduction of the ventilation flow rate of the sectors due to their low thermal conductivity.
  • the ring illustrated in the drawings consists of a circumferential succession of sectors 1 of a suitable abradable ceramic material such as a known composite formed of silicon carbide fibers embedded in a matrix of this same material, having good resistance to high temperatures, low thermal conductivity and good wear properties.
  • a suitable abradable ceramic material such as a known composite formed of silicon carbide fibers embedded in a matrix of this same material, having good resistance to high temperatures, low thermal conductivity and good wear properties.
  • Each ceramic sector 1 has two axial grooves 1a, 1 circumferentially spaced and facing each other. These grooves 1a, 1b allow the attachment of the sector 1 on support fingers 4 projecting in the axial direction of an upstream ferrule 3 connected forwards to the turbine casing at 3a and rearwards to a ferrule downstream 2.
  • the latter has a notch 8 obtained by machining to allow centering of the support fingers 4.
  • a cavity 9 located just above the ring is put at a pressure higher than the pressure prevailing in the vein (by means of air from the bottom of the chamber, taken from the enclosure of the combustion chamber), this which has the effect of preventing hot air from coming up from the vein.
  • the ring sectors 1 are mounted cold pinched slightly upstream and downstream, which leads hot to a slight clearance allowing the evacuation of the pressurization air from the cavity 9 and the ventilation of the ferrules 2 and 3 at their inner radius, as shown by the arrows F1 in FIG. 3.
  • a sheet 7 separates the cavity 9 from a cavity 10.
  • the piloting air is circulated, as shown by the arrows F2, making it possible to control the expansions of the assembly by acting on the temperature of the ferrules 2 and 3.
  • This pilot air from the support ring can be taken from an intermediate stage of the compressor and reused for other ventilation (BP distributor for example) or evacuated in the secondary channel.
  • the support fingers 4 can be cooled by air jets exiting from orifices 11, as shown by the arrows F3 in FIG. 5.
  • This air for ventilation of the support ring can be taken from an intermediate stage of the compressor and evacuated then in the secondary channel.
  • the position of the grooves la, Ib makes it possible to place the fastening fingers 4 in a cooler zone while having a high temperature for the ring sectors 1, the proposed shape allowing effective thermal protection of the fastening.

Landscapes

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

Claims (4)

1. Turbinen-Anstreifring, der an einem im Innern des Turbinengehäuses befestigten ringförmigen Träger montiert ist und aus einer Folge von aneinandergrenzenden Sektoren aus verschleißbarem Keramikwerkstoff besteht, die auf gleicher radialer Höhe auf ihren aneinander zugewandten Seitenflächen erste axiale Nuten (1 c, 1 d) besitzen, in denen Dichtungszungen (6) angeordnet sind, dadurch gekennzeichnet, daß jeder der Sektoren (1) in seinem Mittelbereich eine von seiner radial außen liegenden Seite aus angebrachte Ausnehmung besitzt, daß zwei zweite axiale Nuten (1 a, 1 b), die in Umfangsrichtung Abstand voneinander haben, in einander zugewandter Position in den Seitenflächen der Ausnehmung münden, und daß in diese zweiten Nuten (1a, 1b) Haltefinger (4) eingreifen, die mit einem mit dem Turbinengehäuse verbundenen Ringmantel (3) fest verbunden sind und aufeinanderfolgend das Verhaken der Sektoren (1) bewirken, wobei diese Haltefinger (4) in den genannten zweiten Nuten (1 a, 1b) so aufgenommen sind, daß sie vor den wiedereingeleiteten heißen Gases geschützt sind.
2. Turbinen-Anstreifring nach Anspruch 1, dadurch gekennzeichnet, daß der Ringmantel (2) Öffnungen (11) besitzt, durch die Ströme von Kühlluft dringen und die derart geneigt sind, daß sie diese Ströme auf die Haltefinger (4) leiten.
3. Turbinen-Anstreifring nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß zwischen der radial außen liegenden Seite der Sektoren (1) und der zugeordneten Innenseite eines zylindrischen Ringelements (2) omegaförmige Federn (5) derart angeordnet sind, daß sie einen positiven radialen Kontakt zwischen den Haltefingern (4) und den axialen Nuten (ia, 1b) des Sektors bewirken.
4. Turbinen-Anstreifring nach einem Ansprüche 1 bis 3, dadurch gekennzeichnet, daß der in radialer Richtung außerhalb der Sektoren liegende ringförmige Zwischenraum in zwei Hohlräume (9, 10) unterteilt ist, von denen der eine zum Kühlen der Sektoren und der andere zur Regelung der Ausdehnungen des Stators und damit des daraus resultierenden Spiels zwischen Turbinenrotor und -stator dient, wobei diese beiden Hohlräume (9, 10) durch ein Blech (7) voneinander getrennt sind, dessen Abstützung auf der radial außeren Seite der Sektoren (1) und dessen Abdichtung durch die genannten Federn (5) bewirkt werden.
EP86400133A 1985-01-30 1986-01-23 Anstreifring für eine Gasturbine Expired EP0192516B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8501266 1985-01-30
FR8501266A FR2576637B1 (fr) 1985-01-30 1985-01-30 Anneau de turbine a gaz.

Publications (2)

Publication Number Publication Date
EP0192516A1 EP0192516A1 (de) 1986-08-27
EP0192516B1 true EP0192516B1 (de) 1988-09-28

Family

ID=9315759

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86400133A Expired EP0192516B1 (de) 1985-01-30 1986-01-23 Anstreifring für eine Gasturbine

Country Status (4)

Country Link
US (1) US4676715A (de)
EP (1) EP0192516B1 (de)
DE (1) DE3660826D1 (de)
FR (1) FR2576637B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating

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GB8921003D0 (en) * 1989-09-15 1989-11-01 Rolls Royce Plc Improvements in or relating to shroud rings
GB2245316B (en) * 1990-06-21 1993-12-15 Rolls Royce Plc Improvements in shroud assemblies for turbine rotors
US5181826A (en) * 1990-11-23 1993-01-26 General Electric Company Attenuating shroud support
US5167487A (en) * 1991-03-11 1992-12-01 General Electric Company Cooled shroud support
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5823741A (en) * 1996-09-25 1998-10-20 General Electric Co. Cooling joint connection for abutting segments in a gas turbine engine
FR2815668B1 (fr) * 2000-10-19 2003-01-10 Snecma Moteurs Agencement de liaison d'un anneau de stator de turbine a une entretoise de support
JP2004036443A (ja) * 2002-07-02 2004-02-05 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンシュラウド構造
US7001148B2 (en) * 2002-12-19 2006-02-21 Honeywell International Inc. Replaceable insert for centrifugal blower flow control
US8919781B2 (en) 2003-05-01 2014-12-30 Advanced Technologies Group, Inc. Self-adjusting non-contact seal
US7896352B2 (en) * 2003-05-01 2011-03-01 Justak John F Seal with stacked sealing elements
US8641045B2 (en) * 2003-05-01 2014-02-04 Advanced Technologies Group, Inc. Seal with stacked sealing elements
US7665960B2 (en) 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
FR2906295B1 (fr) * 2006-09-22 2011-11-18 Snecma Dispositif de toles isolantes sur carter pour amelioration du jeu en sommet d'aube
US8059458B2 (en) * 2007-12-31 2011-11-15 Cypress Semiconductor Corporation 3T high density nvDRAM cell
FR2941488B1 (fr) * 2009-01-28 2011-09-16 Snecma Anneau de turbine a encoche anti-rotation
US8534995B2 (en) * 2009-03-05 2013-09-17 United Technologies Corporation Turbine engine sealing arrangement
US8167546B2 (en) * 2009-09-01 2012-05-01 United Technologies Corporation Ceramic turbine shroud support
US9255489B2 (en) * 2012-02-06 2016-02-09 United Technologies Corporation Clearance control for gas turbine engine section
US20150285152A1 (en) * 2014-04-03 2015-10-08 United Technologies Corporation Gas turbine engine and seal assembly therefore
US10801348B2 (en) * 2014-10-14 2020-10-13 Raytheon Technologies Corporation Non-contacting dynamic seal
FR3034454B1 (fr) * 2015-04-01 2018-04-20 Safran Ceramics Ensemble d'anneau de turbine avec liaison inter-secteurs
FR3034453B1 (fr) 2015-04-01 2017-04-28 Herakles Ensemble d'anneau de turbine avec etancheite
US10550709B2 (en) * 2015-04-30 2020-02-04 Rolls-Royce North American Technologies Inc. Full hoop blade track with flanged segments
US10393147B2 (en) * 2015-07-23 2019-08-27 Unison Industries, Llc Fan casing assemblies and method of mounting a cooler to a fan casing
DE102015217078A1 (de) * 2015-09-07 2017-03-09 MTU Aero Engines AG Vorrichtung zum Begrenzen eines Strömungskanals einer Strömungsmaschine
US10370996B2 (en) * 2016-08-23 2019-08-06 United Technologies Corporation Floating, non-contact seal with offset build clearance for load imbalance
RU2639444C1 (ru) * 2017-03-14 2017-12-21 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Узел уплотнения газовой турбины
RU2640974C1 (ru) * 2017-03-31 2018-01-12 Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Узел уплотнения газовой турбины
US10753220B2 (en) 2018-06-27 2020-08-25 Raytheon Technologies Corporation Gas turbine engine component
FR3100561B1 (fr) * 2019-09-10 2023-01-20 Safran Aircraft Engines Fixation d’une virole acoustique a une enveloppe de carter pour une turbomachine d’aeronef
US11066947B2 (en) 2019-12-18 2021-07-20 Rolls-Royce Corporation Turbine shroud assembly with sealed pin mounting arrangement
FR3107549B1 (fr) * 2020-02-24 2022-09-16 Safran Ceram Etanchéité d’une turbine
US11255210B1 (en) 2020-10-28 2022-02-22 Rolls-Royce Corporation Ceramic matrix composite turbine shroud assembly with joined cover plate
US11629607B2 (en) 2021-05-25 2023-04-18 Rolls-Royce Corporation Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments
US11761351B2 (en) 2021-05-25 2023-09-19 Rolls-Royce Corporation Turbine shroud assembly with radially located ceramic matrix composite shroud segments
US11346251B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with radially biased ceramic matrix composite shroud segments
US11441441B1 (en) 2021-06-18 2022-09-13 Rolls-Royce Corporation Turbine shroud with split pin mounted ceramic matrix composite blade track
US11499444B1 (en) 2021-06-18 2022-11-15 Rolls-Royce Corporation Turbine shroud assembly with forward and aft pin shroud attachment
US11319828B1 (en) 2021-06-18 2022-05-03 Rolls-Royce Corporation Turbine shroud assembly with separable pin attachment
US12031443B2 (en) 2022-11-29 2024-07-09 Rolls-Royce Corporation Ceramic matrix composite blade track segment with attachment flange cooling chambers
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating

Also Published As

Publication number Publication date
EP0192516A1 (de) 1986-08-27
FR2576637B1 (fr) 1988-11-18
FR2576637A1 (fr) 1986-08-01
DE3660826D1 (en) 1988-11-03
US4676715A (en) 1987-06-30

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