EP0893577B1 - Kühlvorrichtung für einen Abdeckring in einer Turbomaschine - Google Patents

Kühlvorrichtung für einen Abdeckring in einer Turbomaschine Download PDF

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Publication number
EP0893577B1
EP0893577B1 EP98401872A EP98401872A EP0893577B1 EP 0893577 B1 EP0893577 B1 EP 0893577B1 EP 98401872 A EP98401872 A EP 98401872A EP 98401872 A EP98401872 A EP 98401872A EP 0893577 B1 EP0893577 B1 EP 0893577B1
Authority
EP
European Patent Office
Prior art keywords
wall
orifices
cover
shroud
ring
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 - Lifetime
Application number
EP98401872A
Other languages
English (en)
French (fr)
Other versions
EP0893577A1 (de
Inventor
Daniel Jean Marey
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
SNECMA Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0893577A1 publication Critical patent/EP0893577A1/de
Application granted granted Critical
Publication of EP0893577B1 publication Critical patent/EP0893577B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the subject of the invention is a device for ventilating a turbomachine ring.
  • the problem we are trying to solve here is the machine efficiency loss that the subtraction of the induced ventilation flow: on seeks to limit this flow to the minimum necessary for a good ventilation.
  • the solution chosen consists of arrange in the room behind the ring, and in which the gas supply duct opens, a annular distributor comprising a pierced wall holes and a cover placed between the wall and the conduit and pierced with other orifices, intended for restrict the flow of gas; these orifices lids are fewer and have a section total smaller than the holes in the wall.
  • a stator 1 of a turbomachine is equipped spacers 2 (only one of which is shown) intended to support as many 3 rings which contribute to delimit the gas flow stream of the machine in front of circular stages of moving rotor blades 4.
  • the subject of the invention is an annular housing 5 composed of a cover 6 and a wall 7.
  • the housing 5 is housed in a room 8 delimited by the spacer 2 and ring 3, and it cuts it between this and the outlet 9 of a gas supply circuit relatively fresh from the bottom of the combustion; the rest of the supply circuit is not shown because it is not original, but we may refer to French patent 2,416,345 cited higher for more detail.
  • the integrity of the case 5 is ensured by providing the cover 6 and the wall 7 lateral edges 10 and 11 circular and likewise diameter which are joined in pairs by welds, rivets or other means; the side edges 11 of the wall 7 are also fixed to the spacer 2.
  • the wall 7 is foraminated, that is to say pierced with numerous orifices 12, here substantially more long as wide thanks to their finesse and fairly large wall thickness 7.
  • the cover 6 is pierced by other holes 13, less numerous than those 12 of wall 7 but whose cross section opening hours is also quite limited. They are established at the top of projections 14 obtained by pushing back the material of the cover 6 towards the outside of the case 5 and whose shape is more or less conical so that the orifices 13 communicate with the interior of the housing 5 by pavilions 15 opening towards the wall 7.
  • the gas entering chamber 8 accumulates in front of the housing 5 and passes through the holes 13 then 12 to come and lick the ring 3 before being evacuated in the gas flow stream passing through holes 16 drilled through the ring 3.
  • the constitution of orifices 13 calibrated with precision allows to restrict the gas flow through them without excessively reducing the flow load thanks to the flared shape of the pavilions 15.
  • the projections 14 can however be oriented to favor the mean direction of gas flow in the box 5 to one region or the other of the wall 7.
  • the gas flow is therefore distributed properly in the housing 5 and flows out through the orifices 12, who distribute it by directing it with precision and with the desired spatial distribution towards different portions of the ring 3.
  • the density and direction of the orifices 12 can therefore vary over the wall 7.
  • the conception of the invention is certainly applicable to other parts of the machine than the high pressure turbine rings, and it can also be used with charged gases to warm up the structure on which they are soufflés.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)

Claims (3)

  1. Kühlvorrichtung für einen Turbomaschinenring (3) mit einem Speisekreis (9) für die Zufuhr von aus einem anderen Teil der Turbomaschine stammendem Kühlgas, der in einer Kammer (8) hinter dem Ring (3) mündet, wobei diese Kammer (8) zwischen dem Ring (3) und dem Kreis (9) von einem ringförmigen Verteiler geteilt wird, der eine von Öffnungen (12) durchbrochene Wand (7) äufweist, wobei der Verteiler die Form eines Gehäuses (5) hat und einen Deckel (6) besitzt, der zwischen der Wand (7) und dem Kreis (9) angeordnet und von Öffnungen (13) zur Begrenzung der Gasströmung durchbrochen ist, wobei die Öffnungen (13) des Deckels weniger zahlreich sind und einen kleineren Gesamtquerschnitt haben als die Öffnungen (12) der Wand und auf Vorsprüngen (14) angeordnet sind, die durch Austreiben des Materials des Deckels (16) zum Außenraum des Gehäuses (5) erzeugt werden und Trichter (15) bilden, die sich zu der Wand hin öffnen.
  2. Kühlvorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Wand (7) eine deutlich größere Dicke hat als der Deckel (6) und daß die Öffnungen (12) der Wand mehr lang als breit sind.
  3. Kühlvorrichtung nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß der Deckel und die Wand durch Paare von kreisförmigen Einfassungen (10, 11) gleichen Durchmessers miteinander verbunden sind.
EP98401872A 1997-07-24 1998-07-23 Kühlvorrichtung für einen Abdeckring in einer Turbomaschine Expired - Lifetime EP0893577B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9709399A FR2766517B1 (fr) 1997-07-24 1997-07-24 Dispositif de ventilation d'un anneau de turbomachine
FR9709399 1997-07-24

Publications (2)

Publication Number Publication Date
EP0893577A1 EP0893577A1 (de) 1999-01-27
EP0893577B1 true EP0893577B1 (de) 2003-08-27

Family

ID=9509567

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98401872A Expired - Lifetime EP0893577B1 (de) 1997-07-24 1998-07-23 Kühlvorrichtung für einen Abdeckring in einer Turbomaschine

Country Status (6)

Country Link
US (1) US5964575A (de)
EP (1) EP0893577B1 (de)
JP (1) JP3808211B2 (de)
CA (1) CA2243333C (de)
DE (1) DE69817477T2 (de)
FR (1) FR2766517B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1775426B1 (de) 2005-10-14 2016-05-04 United Technologies Corporation Aktives Spaltkontrollsystem für Gasturbinenantriebe
US11035248B1 (en) 2019-11-25 2021-06-15 General Electric Company Unitary body turbine shrouds including shot peen screens integrally formed therein and turbine systems thereof

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US6139257A (en) * 1998-03-23 2000-10-31 General Electric Company Shroud cooling assembly for gas turbine engine
FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
JP2001221065A (ja) * 2000-02-10 2001-08-17 General Electric Co <Ge> ガスタービンシュラウドのインピンジメント冷却
US6390769B1 (en) * 2000-05-08 2002-05-21 General Electric Company Closed circuit steam cooled turbine shroud and method for steam cooling turbine shroud
FR2816352B1 (fr) * 2000-11-09 2003-01-31 Snecma Moteurs Ensemble de ventilation d'un anneau de stator
FR2819010B1 (fr) * 2001-01-04 2004-05-28 Snecma Moteurs Secteur d'entretoise de support d'anneau de stator de la turbine haute pression d'une turbomachine avec rattrapage de jeux
EP1247943A1 (de) * 2001-04-04 2002-10-09 Siemens Aktiengesellschaft Formstück zur Bildung eines kühlbaren Turbinen-Mantelrings
US6508620B2 (en) 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
KR100444854B1 (ko) * 2001-08-16 2004-08-18 현대자동차주식회사 터보차저의 터빈 블레이드 냉각 구조
EP1400751A1 (de) * 2002-09-17 2004-03-24 Siemens Aktiengesellschaft Brennkammer für eine Gasturbine
ITMI20022418A1 (it) * 2002-11-15 2004-05-16 Nuovo Pignone Spa Assieme migliorato di cassa interna a dispositivo di
US7108479B2 (en) * 2003-06-19 2006-09-19 General Electric Company Methods and apparatus for supplying cooling fluid to turbine nozzles
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
FR2867224B1 (fr) * 2004-03-04 2006-05-19 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
FR2868125B1 (fr) * 2004-03-26 2006-07-21 Snecma Moteurs Sa Turbomachine comprenant deux sous-ensembles assembles sous contrainte axiale
US7118326B2 (en) * 2004-06-17 2006-10-10 Siemens Power Generation, Inc. Cooled gas turbine vane
US7097418B2 (en) * 2004-06-18 2006-08-29 Pratt & Whitney Canada Corp. Double impingement vane platform cooling
DE102005013797A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Wärmestausegment
DE102005013796A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Wärmestausegment
US20070009349A1 (en) * 2005-07-11 2007-01-11 General Electric Company Impingement box for gas turbine shroud
US20070249823A1 (en) * 2006-04-20 2007-10-25 Chemagis Ltd. Process for preparing gemcitabine and associated intermediates
US7607885B2 (en) * 2006-07-31 2009-10-27 General Electric Company Methods and apparatus for operating gas turbine engines
FR2907841B1 (fr) * 2006-10-30 2011-04-15 Snecma Secteur d'anneau de turbine de turbomachine
US7665962B1 (en) 2007-01-26 2010-02-23 Florida Turbine Technologies, Inc. Segmented ring for an industrial gas turbine
US7597533B1 (en) 2007-01-26 2009-10-06 Florida Turbine Technologies, Inc. BOAS with multi-metering diffusion cooling
US8439629B2 (en) * 2007-03-01 2013-05-14 United Technologies Corporation Blade outer air seal
US8439639B2 (en) * 2008-02-24 2013-05-14 United Technologies Corporation Filter system for blade outer air seal
US8100633B2 (en) * 2008-03-11 2012-01-24 United Technologies Corp. Cooling air manifold splash plates and gas turbines engine systems involving such splash plates
US8092146B2 (en) * 2009-03-26 2012-01-10 Pratt & Whitney Canada Corp. Active tip clearance control arrangement for gas turbine engine
FR2955891B1 (fr) * 2010-02-02 2012-11-16 Snecma Secteur d'anneau de turbine de turbomachine
FR2972483B1 (fr) * 2011-03-07 2013-04-19 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
US8998565B2 (en) * 2011-04-18 2015-04-07 General Electric Company Apparatus to seal with a turbine blade stage in a gas turbine
US9080458B2 (en) 2011-08-23 2015-07-14 United Technologies Corporation Blade outer air seal with multi impingement plate assembly
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US20130283814A1 (en) * 2012-04-25 2013-10-31 General Electric Company Turbine cooling system
US9127549B2 (en) * 2012-04-26 2015-09-08 General Electric Company Turbine shroud cooling assembly for a gas turbine system
DE102012016493A1 (de) * 2012-08-21 2014-02-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit prallgekühlten Bolzen der Brennkammerschindeln
CN103775139B (zh) * 2012-10-26 2015-09-23 中航商用航空发动机有限责任公司 涡轮发动机的间隙控制系统及涡轮发动机的间隙控制方法
EP2728255A1 (de) * 2012-10-31 2014-05-07 Alstom Technology Ltd Heißgas-Segmentanordnung
CN103161520A (zh) * 2013-03-01 2013-06-19 哈尔滨汽轮机厂有限责任公司 一种中低热值燃机第一级涡轮护环装置及其拆卸方法
FR3002971B1 (fr) * 2013-03-06 2015-04-17 Snecma Dispositif de ventilation d'un carter de stator d'une turbomachine, comprenant un ajustement sur des circonferences
FR3002972B1 (fr) * 2013-03-06 2015-04-17 Snecma Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale
US20140271154A1 (en) * 2013-03-14 2014-09-18 General Electric Company Casing for turbine engine having a cooling unit
CA2912428C (en) 2013-05-17 2018-03-13 General Electric Company Cmc shroud support system of a gas turbine
EP3080403B1 (de) 2013-12-12 2019-05-01 General Electric Company Trägersystem für cmc-mantel
WO2015138027A2 (en) * 2013-12-17 2015-09-17 United Technologies Corporation Meter plate for blade outer air seal
WO2016025054A2 (en) * 2014-05-29 2016-02-18 General Electric Company Engine components with cooling features
CA2951638A1 (en) 2014-06-12 2015-12-17 General Electric Company Shroud hanger assembly
CA2951425C (en) 2014-06-12 2019-12-24 General Electric Company Shroud hanger assembly
CN106460543B (zh) 2014-06-12 2018-12-21 通用电气公司 多件式护罩悬挂器组件
EP3183431B1 (de) * 2014-08-22 2018-10-10 Siemens Aktiengesellschaft Deckbandkühlsystem für deckbänder neben in schaufeln in gasturbinenmotoren
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
US10337346B2 (en) * 2016-03-16 2019-07-02 United Technologies Corporation Blade outer air seal with flow guide manifold
US11193386B2 (en) * 2016-05-18 2021-12-07 Raytheon Technologies Corporation Shaped cooling passages for turbine blade outer air seal
US10626751B2 (en) * 2017-05-30 2020-04-21 United Technologies Corporation Turbine cooling air metering arrangement
US10612406B2 (en) * 2018-04-19 2020-04-07 United Technologies Corporation Seal assembly with shield for gas turbine engines
FR3082872B1 (fr) * 2018-06-25 2021-06-04 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbomachine
US10914192B2 (en) * 2018-09-25 2021-02-09 Raytheon Technologies Corporation Impingement cooling for gas turbine engine component
US10914186B2 (en) * 2018-12-05 2021-02-09 Raytheon Technologies Corporation BOAS control structure with center support hook
US10830050B2 (en) * 2019-01-31 2020-11-10 General Electric Company Unitary body turbine shrouds including structural breakdown and collapsible features
US11761343B2 (en) * 2019-03-13 2023-09-19 Rtx Corporation BOAS carrier with dovetail attachments
US11248482B2 (en) * 2019-07-19 2022-02-15 Raytheon Technologies Corporation CMC BOAS arrangement
FR3108367B1 (fr) * 2020-03-20 2023-07-21 Safran Aircraft Engines Ensemble de turbine et turbomachine munie d’un tel ensemble

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1775426B1 (de) 2005-10-14 2016-05-04 United Technologies Corporation Aktives Spaltkontrollsystem für Gasturbinenantriebe
US11035248B1 (en) 2019-11-25 2021-06-15 General Electric Company Unitary body turbine shrouds including shot peen screens integrally formed therein and turbine systems thereof

Also Published As

Publication number Publication date
FR2766517A1 (fr) 1999-01-29
EP0893577A1 (de) 1999-01-27
FR2766517B1 (fr) 1999-09-03
JP3808211B2 (ja) 2006-08-09
DE69817477T2 (de) 2004-06-09
JPH1181907A (ja) 1999-03-26
CA2243333A1 (en) 1999-01-24
DE69817477D1 (de) 2003-10-02
US5964575A (en) 1999-10-12
CA2243333C (en) 2007-11-06

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