EP1318274B1 - Hochdruck-Turbinenschaufel mit gekühlter Abströmkante - Google Patents

Hochdruck-Turbinenschaufel mit gekühlter Abströmkante Download PDF

Info

Publication number
EP1318274B1
EP1318274B1 EP02292970A EP02292970A EP1318274B1 EP 1318274 B1 EP1318274 B1 EP 1318274B1 EP 02292970 A EP02292970 A EP 02292970A EP 02292970 A EP02292970 A EP 02292970A EP 1318274 B1 EP1318274 B1 EP 1318274B1
Authority
EP
European Patent Office
Prior art keywords
blade
root
slot
pressure turbine
dawn
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
EP02292970A
Other languages
English (en)
French (fr)
Other versions
EP1318274A1 (de
Inventor
Christian Bariaud
Jacques Boury
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 EP1318274A1 publication Critical patent/EP1318274A1/de
Application granted granted Critical
Publication of EP1318274B1 publication Critical patent/EP1318274B1/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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling

Definitions

  • the present invention relates to the general field of moving blades of a high-pressure turbine of a turbomachine, and more particularly to the cooling air exhaust slots located on the trailing edge of the moving blades of a high-pressure turbine.
  • a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burnt.
  • the gases from this combustion flow downstream into the combustion chamber and then feed a high pressure turbine.
  • the high-pressure turbine has one or more multiple rows of circumferentially spaced movable vanes while around the turbine rotor.
  • the moving blades of the high-pressure turbine are thus subjected to the very high temperatures of the combustion. These temperatures reach values largely higher than those which the blades which can withstand without damage are in contact with these gases, which has the consequence of limiting their lifetime.
  • cooling air which is generally introduced into the dawn by its foot, crosses it in following a path formed by cavities made in the dawn before being ejected through slits opening on the surface of the blade. More precisely, these cooling air exhaust slots are usually distributed along the trailing edge of the dawn, between the foot and the top of the latter, substantially perpendicular to a longitudinal axis of dawn.
  • the present invention therefore aims to overcome such a drawback by proposing a moving blade of a high-pressure turbine having a new geometry of the cooling air exhaust slot the closer to the foot of dawn which does not generate a crack.
  • the invention also aims not to degrade the general mechanical strength of the dawn, part subject to very high mechanical stresses. She aims finally a high-pressure turbine of a turbomachine equipped with such blades mobile.
  • turbomachine comprising at least one circuit cooling composed of at least one cavity extending radially between a summit and a foot of dawn, at least one opening air intake at a radial end of the cavity (ies) for supply the cooling circuit (s) with cooling air, and a plurality of slots opening in the cavity or cavities and opening onto a trailing edge of the blade, the slots being arranged along the edge of flight, between the foot and the top of the dawn, substantially perpendicular to a longitudinal axis of the blade, characterized in that at minus the slit closest to the foot of the blade has an inclination towards the top of the dawn between 10 ° and 30 ° relative to an axis dawn rotation.
  • the inclination of the slot closest to the dawn foot is about 20 °.
  • connection zone To lower the temperature of a connection area between the foot of dawn and a platform defining the vein flow of combustion gases through the high-pressure turbine, the upstream end of the slit closest to the foot of the dawn is formed essentially in this connection zone.
  • Figure 1 shows in perspective a movable blade 10, by example of a high-pressure turbine of a turbomachine. This dawn of longitudinal axis X-X is fixed on a rotor disc (not shown) of the high-pressure turbine via a fitting 12 usually in the shape of a fir tree. It typically comprises a foot 14, a top 16, a leading edge 18 and a trailing edge 20.
  • the fitting 12 is connected to the foot 14 of the blade at the level of a platform 22 defining a wall for the gas flow stream combustion through the high-pressure turbine.
  • the movable blade 10 comprises at least one circuit for internal cooling.
  • This cooling circuit is composed by example of at least one cavity 24 extending radially between the foot 14 and the summit 16 of dawn.
  • This cavity is supplied with air from cooling at one of its radial ends by an opening air intake (not shown).
  • This air intake opening is generally provided at the dawn fitting 12.
  • It is also provided a plurality of slots 26 opening into the cavity 24 and leading to the trailing edge 20 of the blade in order to evacuate the air from cooling flowing into the cavity.
  • These slots 26 for evacuating cooling air is typically distributed along the trailing edge 20, between the foot 14 and the apex 16 of the dawn, substantially perpendicular to the longitudinal axis X-X of the blade.
  • Figure 2 illustrates more precisely the geometry of the slot 28 closest to foot 14 of dawn 10.
  • the slot 28 closest to the foot of the dawn has an inclination towards the vertex 16 of the dawn between 10 ° and 30 ° relative to an axis of dawn rotation (not shown).
  • the inclination of this slit is about 20 °.
  • This particular inclination of the most close to the foot of dawn allows to homogenize the temperature at the level of it and thus remove any hot spot.
  • Air cooling evacuated through this slot covers in fact the entire surface of the slot 28 and lowers the local temperature by around 5%. So any risk of crack at the level of this slot closest to the foot of dawn disappears and the lifespan of dawn is extended.
  • the end upstream 28a of the slot 28 closest to the foot 14 of the dawn is formed essentially in a connection zone 30 between the foot 14 of the blade and the platform 22 on the side of the gas flow stream of combustion so the air exhausted through that slit tends to come cool the connection area 30 by thermal conduction. temperature of the connection zone 30 between the foot 14 of the dawn and the platform 22 is thus lowered by about 1.5%.
  • the sharp angles of the upstream end 28a of the slot 28 are ground to facilitate guiding air evacuated through the slit towards this zone 30.
  • the downstream end 28b of the slot 28 closest to the foot of the blade is not not formed in the connection zone 30, the holding of the blade 10 to the different mechanical stress is not affected by this geometry particular of the slot.

Landscapes

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

Claims (5)

  1. Bewegliche Hochdruck-Turbinenschaufel einer Turbomaschine, die mindestens einen Kühlkreislauf umfasst, der mindestens aus einem Hohlraum (24) besteht, der sich zwischen einer Spitze (16) und einem Fuß (14) der Schaufel (10) radial erstreckt, aus mindestens einer Lufteinlassöffnung an einem radialen Ende des Hohlraumes oder der Hohlräume, um den Kühlkreislauf oder die Kühlkreisläufe mit Kühlluft zu versorgen, und aus einer Vielzahl von Schlitzen (26), die sich in dem Hohlraum oder in den Hohlräumen öffnen und an der Abströmkante (20) der Schaufel einmünden, wobei die Schlitze entlang der Abströmkante zwischen dem Fuß und der Spitze der Schaufel auf eine im Wesentlichen senkrechte Weise zu einer Längsachse (X-X) der Schaufel angeordnet sind, wobei mindestens der Schlitz (28), der dem Fuß der Schaufel am nächsten liegt, eine Neigung in Richtung der Spitze der Schaufel aufweist, dadurch gekennzeichnet, dass die Neigung im Verhältnis zu einer Drehachse der Schaufel zwischen 10° und 30° beträgt.
  2. Schaufel nach Anspruch 1, dadurch gekennzeichnet, dass die Neigung des Schlitzes (28), der dem Fuß der Schaufel am nächsten liegt, ungefähr 20° beträgt.
  3. Schaufel nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass ein stromaufwärts liegendes Ende (28a) des Schlitzes (28), der dem Fuß der Schaufel am nächsten liegt, im Wesentlichen in einem Anschlussbereich (30) zwischen dem Fuß der Schaufel und einer Plattform (22) ausgebildet ist, die eine Wand für einen Ablaufstrom des Verbrennungsgases durch die Hochdruckturbine hindurch definiert.
  4. Schaufel nach Anspruch 3, dadurch gekennzeichnet, dass die scharfen Winkel des stromaufwärts liegenden Endes (28a) des Schlitzes (28), der dem Fuß der Schaufel am nächsten liegt, geschliffen sind.
  5. Hochdruckturbine einer Turbomaschine, dadurch gekennzeichnet, dass sie eine Vielzahl von beweglichen Schaufeln (10) nach irgendeinem der vorhergehenden Ansprüche umfasst.
EP02292970A 2001-12-10 2002-12-03 Hochdruck-Turbinenschaufel mit gekühlter Abströmkante Expired - Lifetime EP1318274B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0115904 2001-12-10
FR0115904A FR2833298B1 (fr) 2001-12-10 2001-12-10 Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression

Publications (2)

Publication Number Publication Date
EP1318274A1 EP1318274A1 (de) 2003-06-11
EP1318274B1 true EP1318274B1 (de) 2004-09-22

Family

ID=8870271

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02292970A Expired - Lifetime EP1318274B1 (de) 2001-12-10 2002-12-03 Hochdruck-Turbinenschaufel mit gekühlter Abströmkante

Country Status (9)

Country Link
US (1) US6830431B2 (de)
EP (1) EP1318274B1 (de)
JP (1) JP4012054B2 (de)
CA (1) CA2412989C (de)
DE (1) DE60201325T2 (de)
ES (1) ES2225740T3 (de)
FR (1) FR2833298B1 (de)
RU (1) RU2297537C2 (de)
UA (1) UA80246C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4136323B1 (de) * 2020-06-22 2024-05-29 Siemens Energy Global GmbH & Co. KG Turbinenschaufel und zugehöriges herstellungsverfahren

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2864990B1 (fr) * 2004-01-14 2008-02-22 Snecma Moteurs Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression
US7503749B2 (en) * 2005-04-01 2009-03-17 General Electric Company Turbine nozzle with trailing edge convection and film cooling
FR2887287B1 (fr) * 2005-06-21 2007-09-21 Snecma Moteurs Sa Circuits de refroidissement pour aube mobile de turbomachine
KR100847523B1 (ko) * 2006-12-29 2008-07-22 엘지전자 주식회사 터보팬
US8002525B2 (en) * 2007-11-16 2011-08-23 Siemens Energy, Inc. Turbine airfoil cooling system with recessed trailing edge cooling slot
FR2924156B1 (fr) * 2007-11-26 2014-02-14 Snecma Aube de turbomachine
US8157504B2 (en) * 2009-04-17 2012-04-17 General Electric Company Rotor blades for turbine engines
FR2954798B1 (fr) 2009-12-31 2012-03-30 Snecma Aube a ventilation interieure
US8608429B2 (en) * 2010-05-28 2013-12-17 General Electric Company System and method for enhanced turbine wake mixing via fluidic-generated vortices
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE794195A (fr) * 1972-01-18 1973-07-18 Bbc Sulzer Turbomaschinen Aube directrice refroidie pour des turbines a gaz
GB2121483B (en) * 1982-06-08 1985-02-13 Rolls Royce Cooled turbine blade for a gas turbine engine
US4601638A (en) * 1984-12-21 1986-07-22 United Technologies Corporation Airfoil trailing edge cooling arrangement
US5403158A (en) * 1993-12-23 1995-04-04 United Technologies Corporation Aerodynamic tip sealing for rotor blades
DE69718673T2 (de) * 1996-06-28 2003-05-22 United Technologies Corp Kühlbare schaufelstruktur für eine gasturbine
CA2334071C (en) * 2000-02-23 2005-05-24 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4136323B1 (de) * 2020-06-22 2024-05-29 Siemens Energy Global GmbH & Co. KG Turbinenschaufel und zugehöriges herstellungsverfahren

Also Published As

Publication number Publication date
RU2297537C2 (ru) 2007-04-20
CA2412989C (fr) 2008-09-23
US6830431B2 (en) 2004-12-14
JP4012054B2 (ja) 2007-11-21
DE60201325T2 (de) 2005-03-17
CA2412989A1 (fr) 2003-06-05
US20030108425A1 (en) 2003-06-12
UA80246C2 (uk) 2007-09-10
JP2003193804A (ja) 2003-07-09
FR2833298A1 (fr) 2003-06-13
FR2833298B1 (fr) 2004-08-06
EP1318274A1 (de) 2003-06-11
DE60201325D1 (de) 2004-10-28
ES2225740T3 (es) 2005-03-16

Similar Documents

Publication Publication Date Title
EP1726783B1 (de) Hohle Laufschaufel für die Turbine eines Gasturbinentriebwerks, mit einem Hohlraum
CA2652679C (fr) Aubes pour roue a aubes de turbomachine avec rainure pour le refroidissement
CA2493094C (fr) Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine
EP1612374B1 (de) Turbinenstatorschaufel mit verbesserter Kühlung
CA2550442C (fr) Circuits de refroidissement pour aube mobile de turbomachine
EP1333155A1 (de) Kühlung der Abströmkante einer Hochdruckturbinenlaufschaufel
CA2834213C (fr) Dispositif d'etancheite pour distributeur de turbine de turbomachine
EP1318274B1 (de) Hochdruck-Turbinenschaufel mit gekühlter Abströmkante
CA2569563C (fr) Aube de turbine a refroidissement et a duree de vie ameliores
EP1790819A1 (de) Kühlkreislauf einerTurbinenschaufel
EP1598523A1 (de) Wandstruktur für hohle Gasturbinenschaufeln zur Verbesserung des Wärmeübergangs
WO2013001240A1 (fr) Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz
FR2981979A1 (fr) Roue de turbine pour une turbomachine
CA2456705C (fr) Plate-forme annulaire de distributeur d'une turbine basse-pression de turbomachine
CA2456696C (fr) Aubes de turbine refroidie a fuite d'air de refroidissement reduite
FR3075869A1 (fr) Roue mobile de turbine pour turbomachine d'aeronef, comprenant un anneau d'etancheite retenu radialement par des excroissances sur l'echasse des aubes
FR3066783B1 (fr) Chemise pour aube de turbine a refroidissement optimise
EP3420198B1 (de) Statoranordnung für turbomaschinenverdichter eines flugzeugs mit luftabsaugungsöffnungen mit gestreckter form in umfangsrichtung
EP3768949B1 (de) Turbinenleitschaufel mit prallkühlmerkmalen
FR3090032A1 (fr) Aube pour roue de turbomachine
FR3127021A1 (fr) Aube mobile pour turbine de turbomachine, comprenant une échasse équipée d’excroissances de retenue radiale de l’aube
EP3942158A1 (de) Mit optimiertem kühlkreislauf ausgestattete turbinentriebwerksschaufel

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: 20021207

AK Designated contracting states

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: FRENCH

REF Corresponds to:

Ref document number: 60201325

Country of ref document: DE

Date of ref document: 20041028

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2225740

Country of ref document: ES

Kind code of ref document: T3

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

Effective date: 20050623

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

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

Ref country code: ES

Payment date: 20121205

Year of fee payment: 11

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20150407

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

Ref country code: ES

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

Effective date: 20131204

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

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

Ref country code: DE

Payment date: 20211117

Year of fee payment: 20

Ref country code: SE

Payment date: 20211119

Year of fee payment: 20

Ref country code: GB

Payment date: 20211118

Year of fee payment: 20

Ref country code: FR

Payment date: 20211118

Year of fee payment: 20

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

Ref country code: IT

Payment date: 20211117

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 60201325

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20221202

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

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20221202

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG