EP0785338A1 - Kühleinrichtung für eine Turbinenscheibe - Google Patents

Kühleinrichtung für eine Turbinenscheibe Download PDF

Info

Publication number
EP0785338A1
EP0785338A1 EP97400078A EP97400078A EP0785338A1 EP 0785338 A1 EP0785338 A1 EP 0785338A1 EP 97400078 A EP97400078 A EP 97400078A EP 97400078 A EP97400078 A EP 97400078A EP 0785338 A1 EP0785338 A1 EP 0785338A1
Authority
EP
European Patent Office
Prior art keywords
flange
channels
outer ring
circuit
stator
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
EP97400078A
Other languages
English (en)
French (fr)
Other versions
EP0785338B1 (de
Inventor
Christian Largillier
Gérard Jacques Stangalini
Marc Roger Marchi
Laurent Palmisano
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
SNECMA SAS
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, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0785338A1 publication Critical patent/EP0785338A1/de
Application granted granted Critical
Publication of EP0785338B1 publication Critical patent/EP0785338B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Definitions

  • the invention relates to a device for cooling a turbine disc.
  • the high pressure turbine 1 begins in a disc 2 carrying a first stage of movable vanes 3 and fixed to the rotor 4.
  • This disc 2 is located downstream of a combustion chamber 5 formed in a stator 6 surrounding the rotor 4 and which is itself located downstream of a high pressure compressor 7.
  • the gases resulting from the combustion of the fuel in the chamber 5 very strongly heat the disc 2, which must therefore be cooled vigorously to maintain the material which composes it at a temperature compatible with the maintenance of its mechanical resistance properties.
  • the means used consist of two ventilation circuits I and II of cooler air: the first of them I, illustrated by the arrows in solid lines, uses air drawn just upstream from the combustion chamber 5 and which passes through a chamber bottom volume 28 before leaving it via orifices 8 in order to enter injection chambers 9 from which the air exits by high pressure injectors 10 which accelerate and propel it at great speed speed towards side 14 of disc 2.
  • the second air flow II is taken just after the high pressure compressor 7 and passes through a chamber 16 between the rotor 4 and the stator 6 from which it exits by a labyrinth seal or with a brush 17 thrown between these parts and more precisely composed of wipers 18, that is to say circular ridges erected on the rotor 4, which rub on an abradable material 19 fixed to the stator 6, that is to say to say a soft matter which they dig with the liking of differential expansions with the various modes of the machine.
  • the air pressure projects the air out of the chamber 16 and into an annular channel 20 of divergent orientation, contiguous to a part of the chamber bottom 28 over a large part of its length and from where the air exits via upper injectors 36 which open in front of a radially outer ring 22 of the turbine disc 2, in fact belonging to a side surface 29 of the flange 13 secured to this disc.
  • the air of the second ventilation circuit exerts significant refrigeration on the outer ring 22 by reaching this area close to the combustion gases and therefore more strongly heated.
  • the need to cool the entire disc 2 but especially its periphery justifies the duality of the cooling circuits, the air of which can moreover come from other places of the machine.
  • part of the air from the first ventilation circuit does not pass through the orifices 12 but bypasses the flange 13 from the outside and passes through a labyrinth or brush seal 23, which is roughly similar. to the previous 17 and composed like him of wipers 24 erected on the flange 13 and a layer of abradable 25 welded on a surface of the stator 6.
  • the centrifugal forces that the flange 13 exerts on this portion of the first flow straightens it like the previous portion and makes it run along the flank surface 29 to finally cross the flow of the second ventilation circuit in front of the external crown 22.
  • the origin of the invention is based on the observation that this situation was not ideal because the air stream from circuit I is significantly warmer than that of circuit II (around 50 ° C).
  • the invention consists in adding parts whose function is to channel the flows so that their mixing is excluded and that the air of the circuit II originating from the upper injectors 36 reaches the outer ring 22 without hindrance; this air of circuit II is appreciably cooler than that of the first circuit I, because the labyrinth or brush seal 17 which is associated with it, heats the air less than the labyrinth seal 23, of larger diameter, and the air of the first circuit I is centrifuged at the outlet of the labyrinth 23, therefore compressed, which also heats it up.
  • the invention therefore consists of a device for cooling a turbine disc, comprising first and second air ventilation circuits originating from a stator and opening respectively in front of an internal crown and a outer crown radially of a flank surface of the disc, characterized in that it comprises a part located in front of the outer crown, crossing first channels substantially parallel to the flank surface of the disc and second channels extending the second ventilation circuit, crossing the first channels without cutting them, and ending in front of the outer crown.
  • the fundamental element of the invention is a distributor ring 30 integral with the stator 6 and located in front of the outer ring 22 to be cooled, not far from it.
  • the distributor crown 30 is traversed by axial channels 32 which extend the upper injectors 36 to terminate in front of the external crown 22, and the channels 32 are separated by substantially radial channels 31 which cross the previous ones without cutting them, as shown in detail in section of figure 3.
  • the interior of the distributor crown 30 is arranged to minimize pressure losses; this is how the axial channels 32 can be connected to injectors 36 of oblique direction, bent in the direction of travel of the disc 2.
  • the ventilation air of the second circuit II borrows the axial channels 32 and is therefore not affected by the air of circuit I, which passes through the radial channels 31; the mixing of the flows only occurs at the periphery of the disc 2, beyond the outer ring 22.
  • the flange 13 can be constructed with a wiper 33 on its flank surface 14, that is to say a crest whose free end 34 is close to the distributor crown 30 and whose purpose is to guide the air in the flow I running along the side surface 29 of the flange 13 towards the radial channels 31, without allowing it to slide to the outer ring 22.
  • the turbine disk 2 is brought to a temperature above 650 ° C in the known machine.
  • the use of the invention makes it possible to reduce this temperature by several tens of degrees for the flange 13. Progress is important if we consider the high level of quality already achieved with existing engines; it can be exploited by using less expensive materials to build the disc 2 and its flange 13, or by reducing the cooling rates.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)
EP97400078A 1996-01-18 1997-01-16 Kühleinrichtung für eine Turbinenscheibe Expired - Lifetime EP0785338B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9600521A FR2743844B1 (fr) 1996-01-18 1996-01-18 Dispositif de refroidissement d'un disque de turbine
FR9600521 1996-01-18

Publications (2)

Publication Number Publication Date
EP0785338A1 true EP0785338A1 (de) 1997-07-23
EP0785338B1 EP0785338B1 (de) 2000-03-15

Family

ID=9488209

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97400078A Expired - Lifetime EP0785338B1 (de) 1996-01-18 1997-01-16 Kühleinrichtung für eine Turbinenscheibe

Country Status (5)

Country Link
US (1) US5800125A (de)
EP (1) EP0785338B1 (de)
CA (1) CA2195040C (de)
DE (1) DE69701405T2 (de)
FR (1) FR2743844B1 (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1367225A2 (de) 2002-05-30 2003-12-03 Mitsubishi Heavy Industries, Ltd. Kühlungsanordnung in einer Gasturbine und Verfahren zum Anzapfen von Luft
EP1741874A2 (de) * 2005-07-01 2007-01-10 Rolls-Royce plc Aufbauanordnung für Turbinenschaufeln
EP2048324A1 (de) * 2007-10-11 2009-04-15 Snecma Turbinenstator für Turbotriebwerk eines Luftfahrzeugs, der mit einer Schwingungsdämpfungsvorrichtung ausgestattet ist
EP1911937A3 (de) * 2006-10-14 2012-09-05 Rolls-Royce plc Lufthohlraumanordnung eines Gasturbinentriebwerks
KR101232609B1 (ko) 2010-12-21 2013-02-13 두산중공업 주식회사 가스터빈 엔진의 로터 블레이드 프리 스월 냉각 장치
EP2942483A1 (de) * 2014-04-01 2015-11-11 United Technologies Corporation Belüftete bordseitige tangenzialdüse für einen gasturbinenmotor
WO2018020131A1 (fr) * 2016-07-29 2018-02-01 Safran Aircraft Engines Turbine comprenant un systeme de ventilation entre rotor et stator
RU178381U1 (ru) * 2017-08-16 2018-04-02 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Амортизатор для гашения вибраций статора турбореактивного двигателя
WO2019168590A1 (en) * 2018-02-27 2019-09-06 Siemens Aktiengesellschaft Gas turbine engine with turbine cooling air delivery system

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19962244A1 (de) * 1999-12-22 2001-06-28 Rolls Royce Deutschland Kühlluft-Führungssystem im Hochdruck-Turbinenabschnitt eines Gasturbinen Triebwerkes
FR2881472B1 (fr) * 2005-01-28 2011-07-15 Snecma Moteurs Circuit de ventilation d'un rotor de turbine haute pression dans un moteur a turbine a gaz
GB2426289B (en) * 2005-04-01 2007-07-04 Rolls Royce Plc Cooling system for a gas turbine engine
US7445424B1 (en) * 2006-04-22 2008-11-04 Florida Turbine Technologies, Inc. Passive thermostatic bypass flow control for a brush seal application
JP5134570B2 (ja) * 2009-02-23 2013-01-30 三菱重工業株式会社 タービンの冷却構造およびガスタービン
US8727703B2 (en) * 2010-09-07 2014-05-20 Siemens Energy, Inc. Gas turbine engine
DE102011101729B3 (de) * 2011-05-17 2012-09-27 Adc Gmbh Verteilerleiste und Verteilerblock mit mindestens zwei Verteilerleisten
EP3130750B1 (de) * 2015-08-14 2018-03-28 Ansaldo Energia Switzerland AG Gasturbinenkühlsystem

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2292868A1 (fr) * 1974-11-27 1976-06-25 Gen Electric Systeme de joints a labyrinthe pour turbine a gaz
FR2439872A1 (fr) * 1978-10-26 1980-05-23 Rolls Royce Turbine refroidie par air pour moteur a turbine a gaz
GB2042643A (en) * 1979-01-02 1980-09-24 Rolls Royce Cooled Gas Turbine Engine
GB2135394A (en) * 1983-02-22 1984-08-30 Gen Electric Cooling gas turbine engines
GB2266345A (en) * 1992-04-23 1993-10-27 Snecma Ventilation circuit for the compressor and turbine discs of a turbomachine.
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2292868A1 (fr) * 1974-11-27 1976-06-25 Gen Electric Systeme de joints a labyrinthe pour turbine a gaz
FR2439872A1 (fr) * 1978-10-26 1980-05-23 Rolls Royce Turbine refroidie par air pour moteur a turbine a gaz
GB2042643A (en) * 1979-01-02 1980-09-24 Rolls Royce Cooled Gas Turbine Engine
GB2135394A (en) * 1983-02-22 1984-08-30 Gen Electric Cooling gas turbine engines
GB2184167A (en) * 1983-02-22 1987-06-17 Gen Electric Cooling gas turbine engine components
GB2266345A (en) * 1992-04-23 1993-10-27 Snecma Ventilation circuit for the compressor and turbine discs of a turbomachine.
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1367225A3 (de) * 2002-05-30 2010-01-20 Mitsubishi Heavy Industries, Ltd. Kühlungsanordnung in einer Gasturbine und Verfahren zum Anzapfen von Luft
EP1367225A2 (de) 2002-05-30 2003-12-03 Mitsubishi Heavy Industries, Ltd. Kühlungsanordnung in einer Gasturbine und Verfahren zum Anzapfen von Luft
EP1741874A3 (de) * 2005-07-01 2014-01-22 Rolls-Royce plc Aufbauanordnung für Turbinenschaufeln
EP1741874A2 (de) * 2005-07-01 2007-01-10 Rolls-Royce plc Aufbauanordnung für Turbinenschaufeln
EP1911937A3 (de) * 2006-10-14 2012-09-05 Rolls-Royce plc Lufthohlraumanordnung eines Gasturbinentriebwerks
EP2048324A1 (de) * 2007-10-11 2009-04-15 Snecma Turbinenstator für Turbotriebwerk eines Luftfahrzeugs, der mit einer Schwingungsdämpfungsvorrichtung ausgestattet ist
FR2922263A1 (fr) * 2007-10-11 2009-04-17 Snecma Sa Stator de turbine pour turbomachine d'aeronef integrant un dispositif d'amortissement de vibrations
US8133010B2 (en) 2007-10-11 2012-03-13 Snecma Turbine stator for aircraft turbine engine including a vibration damping device
RU2474697C2 (ru) * 2007-10-11 2013-02-10 Снекма Статор турбины для газотурбинного двигателя летательного аппарата, содержащий устройство для амортизации вибраций
KR101232609B1 (ko) 2010-12-21 2013-02-13 두산중공업 주식회사 가스터빈 엔진의 로터 블레이드 프리 스월 냉각 장치
EP2942483A1 (de) * 2014-04-01 2015-11-11 United Technologies Corporation Belüftete bordseitige tangenzialdüse für einen gasturbinenmotor
US10697321B2 (en) 2014-04-01 2020-06-30 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
US10920611B2 (en) 2014-04-01 2021-02-16 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
WO2018020131A1 (fr) * 2016-07-29 2018-02-01 Safran Aircraft Engines Turbine comprenant un systeme de ventilation entre rotor et stator
FR3054606A1 (fr) * 2016-07-29 2018-02-02 Safran Aircraft Engines Turbine comprenant un systeme de ventilation entre rotor et stator
US10808537B2 (en) 2016-07-29 2020-10-20 Safran Aircraft Engines Turbine comprising a ventilation system between rotor and stator
RU178381U1 (ru) * 2017-08-16 2018-04-02 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Амортизатор для гашения вибраций статора турбореактивного двигателя
WO2019168590A1 (en) * 2018-02-27 2019-09-06 Siemens Aktiengesellschaft Gas turbine engine with turbine cooling air delivery system

Also Published As

Publication number Publication date
CA2195040A1 (fr) 1997-07-19
DE69701405D1 (de) 2000-04-20
FR2743844B1 (fr) 1998-02-20
CA2195040C (fr) 2005-11-15
US5800125A (en) 1998-09-01
EP0785338B1 (de) 2000-03-15
DE69701405T2 (de) 2000-08-03
FR2743844A1 (fr) 1997-07-25

Similar Documents

Publication Publication Date Title
EP0785338B1 (de) Kühleinrichtung für eine Turbinenscheibe
EP1881181B1 (de) Strömungsmaschine
EP0651137B1 (de) Turbomaschine mit System zur Heizung der Rotorscheiben in der Beschleunigungsphase
EP1882826B1 (de) System zur Lüftung eines Hohlraums stromabwärts eines Zentrifugalverdichterrads
EP1881182B1 (de) Kühlsystem für den Hohlraum hinter dem Rad eines Radialverdichters
EP2440746B1 (de) Turbinenmotor mit verbesserter vorrichtung zur einstellung der strömungsgeschwindigkeit eines am ausgang eines hochdruckverdichters abgezapften kühlluftstroms
EP1882815B1 (de) Strömungsmaschine mit einem Kühlsystem für die Rückseite eines Zentrifugalverdichterrads
CA2715209A1 (fr) Ventilation d'une roue de turbine dans une turbomachine
EP1785671A1 (de) Belüfteter Brennkammerdom
FR2782539A1 (fr) Turbomachine comportant un dispositif de fourniture de gaz pressurise
FR2986275A1 (fr) Procede d'ejection de gaz d'echappement de turbine a gaz et ensemble d'echappement de configuration optimisee
EP0177408A1 (de) Vorrichtung für die automatische Regelung des Spiels einer Labyrinthdichtung einer Turbomaschine
FR2955145A1 (fr) Distributeur de turbine haute pression d'un turboreacteur
FR2707698A1 (fr) Turbomachine munie d'un moyen de soufflage d'air sur un élément de rotor.
FR2992347A1 (fr) Recepteur de turbomachine d'aeronef a doublet d'helices contrarotatives non carenees, comprenant une turbine libre exterieure a maintien renforce
FR2630162A1 (fr) Systeme d'antigivrage de cone d'entree pour turbomoteurs a gaz
EP4081698B1 (de) Turbine, die einen inneren sekundärraum aufweist, der mit rippen zum korrigieren der kreiselbewegung eines luftstroms ausgestattet ist
FR3127521A1 (fr) Carter d’injection d’air de refroidissement pour turbine de turbomachine
CA2997939A1 (fr) Dispositif de ventilation d'un carter de turbine d'une turbomachine
FR2686032A1 (fr) Dispositif de pulverisation d'un liquide, notamment d'un combustible liquide dans un bruleur.
CA3099889A1 (fr) Dispositif de refroidissement d'un carter de turbomachine
EP3969813B1 (de) Brennkammer mit mitteln zur kühlung einer ringförmigen mantelzone stromabwärts eines abzugs
FR3005109A1 (fr) Volute a deux volumes pour turbine a gaz
WO2024194566A1 (fr) Carter d'injection d'air pour turbomachine
FR3125844A1 (fr) Turbomachine comportant un cône de sortie intégrant des composants refroidis par circulation d’un flux de refroidissement

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19970203

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19981208

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 69701405

Country of ref document: DE

Date of ref document: 20000420

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20000410

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120517 AND 20120523

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20141219

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20141218

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20160111

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69701405

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160802

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160116

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717