EP1598523A1 - Wandstruktur für hohle Gasturbinenschaufeln zur Verbesserung des Wärmeübergangs - Google Patents

Wandstruktur für hohle Gasturbinenschaufeln zur Verbesserung des Wärmeübergangs Download PDF

Info

Publication number
EP1598523A1
EP1598523A1 EP05290838A EP05290838A EP1598523A1 EP 1598523 A1 EP1598523 A1 EP 1598523A1 EP 05290838 A EP05290838 A EP 05290838A EP 05290838 A EP05290838 A EP 05290838A EP 1598523 A1 EP1598523 A1 EP 1598523A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
cavity
dawn
depressions
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
EP05290838A
Other languages
English (en)
French (fr)
Other versions
EP1598523B1 (de
Inventor
Stéphan Daux
Chantal Giot
Hugues Joubert
Benjamin Sauthier
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 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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1598523A1 publication Critical patent/EP1598523A1/de
Application granted granted Critical
Publication of EP1598523B1 publication Critical patent/EP1598523B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface

Definitions

  • the present invention relates to the general field of turbomachine gas turbine blade cooling. It aims more particularly to improve the cooling of a blade provided with a high form ratio cooling cavity.
  • cooling circuits are unsuitable for so-called "fine and long" blades, ie blades having a width (maximum distance separating the intrados from the extrados of the dawn) much smaller than their radial height (distance separating the head from the dawn summit).
  • the main object of the present invention is therefore to overcome such disadvantages by proposing a cooling circuit for a dawn gas turbine, and more particularly a blade of "fine” type and long, “allowing efficient cooling of the dawn and which is of easy manufacture.
  • a gas turbine blade for turbomachine, comprising a cooling circuit comprising at least less a high aspect ratio cooling cavity extending radially between a foot and a blade tip and at least one air intake opening at a lower radial end of the cavity for supplying it with cooling air, characterized in that least one of the walls of the cooling cavity is provided with a plurality of depressions so as to disturb the airflow of cooling in the cavity and increasing heat exchange.
  • a cooling cavity is considered to have a high aspect ratio when, in cross-section, it has a high dimension (length) at least three times greater than the other (width).
  • the recesses are motives with recesses of matter. Of such depressions thus make it possible to disturb the internal flow without to obstruct it.
  • the cooling circuit of the dawn according to the invention also makes it possible to obtain efficient cooling of dawn, with lower head losses and low concentrations of constraints therefore to better mechanical strength. The manufacture of such dawn is further simplified since its cooling circuit can be easily obtained from foundry.
  • the walls of the cooling cavity can be advantageously devoid of flow-disrupting patterns at added material of the type pins or bridges. Indeed, the presence of penetrations on at least one of the walls of the cavity of cooling is sufficient to disturb the internal flow of air circulating in this one.
  • the cooling circuit can be devoid of air emissions on the faces of the dawn. In that case, the evacuation of the air circulating in the cooling cavity is carried out at the top of dawn.
  • the present invention preferably applies to a dawn having a ratio between its width and its radial height between the foot and the peak between 0.01 and 0.25.
  • Dawn can also be a connection between the depth depressions and the width of the cooling cavity included between 0.15 and 0.65.
  • the depressions can be made on the walls of the cooling cavity of the the intrados and the extrados side of the dawn. They can be substantially aligned along a radial axis of the blade or staggered by compared to this same axis. Moreover, they can be practiced only on a part of the dawn, for example on a lower part of it.
  • the recesses of the cooling cavity can have a substantially spherical or conical cross section.
  • the blade 10 of radial axis XX 'shown in FIGS. 1 and 2 is a turbomachine turbine high-pressure turbine blade. Good understood, the invention can also be applied to other blades of the turbomachine, for example at the blades of the low-pressure turbine of it.
  • the blade 10 has an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14.
  • the blade root 12 is intended to be mounted on a disk 16 of the rotor of the high pressure turbine.
  • the dawn apex 14 may comprise sealing strips 17 arranged opposite a abradable coating 19 mounted on the housing (not shown) of the high pressure turbine.
  • the aerodynamic surface has four distinct zones: a leading edge 18 disposed opposite the flow of hot gases from of the combustion chamber of the turbomachine, a trailing edge 20 opposite to the leading edge 18, a lateral face 22 and a face lateral extrados 24, these lateral faces 22, 24 connecting the leading edge 18 at the trailing edge 20.
  • the blade 10 is provided with a cooling circuit comprising at least one high form ratio cooling cavity 26 extending radially between the foot 12 and the blade tip 14 and at minus an air inlet opening 28 at a radial end bottom of the cavity 26 (that is to say at the level of the blade root 12) for supply it with cooling air
  • high form ratio cavity is meant a cavity which has, in cross section, a dimension (length L1 ) at least three times, and preferably at least five times, greater than the other (width I1 ). This characteristic of the cavity 26 is particularly visible in FIG.
  • the cooling cavity 26 is delimited by an intrados wall 26a disposed on the intrados side 22 of the blade and by an extrados wall 26b disposed on the extrados side 24 of the blade. These walls 26a, 26b meet at the two axial ends of the cavity 26 and the distance between them represents the width I1 of the cavity.
  • the cooling circuit of the blade 10 of FIGS. 1 and 2 has a single cavity 26 which extends axially from the edge 18 to the trailing edge 20 of the dawn 10. However, imagine that the dawn has several cooling cavities to high form ratio.
  • At least one of the walls 26a, 26b of the cavity 26 of the dawn 10 is provided with a plurality of depressions 30 so as to disturb the air flow of cooling in said cavity and to increase the exchanges of heat.
  • the recesses 30 are patterns detrimental to the flow of material removed, that is to say that they do not require no addition of material.
  • the two walls 26a, 26b of the cavity 26 are provided with recesses 30. It can however be imagined that the recesses are only practiced on one of them.
  • the walls 26a, 26b of the cooling cavity 26 are devoid of added matter flow disruptors.
  • the walls 26a, 26b of the cavity 26 do not comprise any disrupter type pins or bridges.
  • the unique presence of depressions 30 is sufficient to ensure effective cooling of the blade 10.
  • the dawn cooling circuit is devoid of air emissions on the faces of the blade 10 (that is to say on the lateral faces intrados 22 and extrados 24, as well as the leading edges 18 and trailing 20 thereof).
  • the cooling air circulating in the cavity 26 of the cooling circuit is entirely evacuated by the blade tip 14, for example at the wipers 17.
  • the cooling circuit has several cavities to high aspect ratio, these are preferably independent of each other: they are all individually supplied with air by the dawn foot 12 and the air circulating in them is entirely evacuated by the dawn 14.
  • the invention is preferably applied to a so-called “fine and long" blade 10 as illustrated in FIG. 1, that is to say having a ratio between its width I2 (maximum distance separating the intrados face 22 of the extrados face 24 dawn, Figure 2, also called master torque) and its radial height h (Figure 1) between the foot 12 and the blade tip 14 between 0.01 and 0.25.
  • the blade 10 has a ratio between the depth P of the depressions 30 (FIGS. 5 and 6) and the width I1 of the cooling cavity 26 (FIG. and 0.65.
  • the recesses 30 of the cooling cavity 26 of the blade 10 may be arranged in staggered relation to the radial axis XX ' dawn ( Figures 1 and 3). Alternatively, the depressions 30 of the cooling cavity 26 may be substantially aligned along the axis radial XX 'of the dawn ( Figure 4).
  • the depressions 30 of the cooling cavity 26 can be made only at a lower part of the blade 10, for example at a radial height representing approximately 30% of the radial height. total h of the dawn between its foot 12 and its top 14.
  • the depressions can also be practiced over all or part of the radial height of the blade.
  • the recesses 30 of the cooling cavity 26 can have a substantially spherical cross section (Figure 5) or substantially conical ( Figure 6). We can also imagine any other shape for their section: square, cylindrical, drop-shaped, etc.
  • the size, the depth P and the spacing between two adjacent depressions is also variable depending on the level of disturbance that is sought to obtain.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05290838.1A 2004-05-18 2005-04-15 Wandstruktur für hohle Gasturbinenschaufeln zur Verbesserung des Wärmeübergangs Active EP1598523B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0405397 2004-05-18
FR0405397A FR2870560B1 (fr) 2004-05-18 2004-05-18 Circuit de refroidissement a cavite a rapport de forme eleve pour aube de turbine a gaz

Publications (2)

Publication Number Publication Date
EP1598523A1 true EP1598523A1 (de) 2005-11-23
EP1598523B1 EP1598523B1 (de) 2016-01-20

Family

ID=34942141

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290838.1A Active EP1598523B1 (de) 2004-05-18 2005-04-15 Wandstruktur für hohle Gasturbinenschaufeln zur Verbesserung des Wärmeübergangs

Country Status (7)

Country Link
US (1) US7513737B2 (de)
EP (1) EP1598523B1 (de)
JP (1) JP4854985B2 (de)
CA (1) CA2504168C (de)
FR (1) FR2870560B1 (de)
RU (1) RU2388915C2 (de)
UA (1) UA86580C2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3052990A1 (fr) * 2016-06-28 2017-12-29 Snecma Circuit de refroidissement d'une aube de turbomachine
EP4092249A1 (de) * 2021-05-19 2022-11-23 Rolls-Royce plc Düsenleitschaufel

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4831816B2 (ja) * 2006-03-02 2011-12-07 三菱重工業株式会社 ガスタービンの翼冷却構造
US7722327B1 (en) * 2007-04-03 2010-05-25 Florida Turbine Technologies, Inc. Multiple vortex cooling circuit for a thin airfoil
US8894367B2 (en) * 2009-08-06 2014-11-25 Siemens Energy, Inc. Compound cooling flow turbulator for turbine component
EP2354453B1 (de) * 2010-02-02 2018-03-28 Siemens Aktiengesellschaft Turbinenmotorkomponente zur adaptiven Kühlung
US8770936B1 (en) * 2010-11-22 2014-07-08 Florida Turbine Technologies, Inc. Turbine blade with near wall cooling channels
RU2522156C2 (ru) * 2012-07-17 2014-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Юго-Западный государственный университет" (ЮЗ ГУ) Теплотрубный контур охлаждения лопатки турбины
US9718735B2 (en) 2015-02-03 2017-08-01 General Electric Company CMC turbine components and methods of forming CMC turbine components
US10605170B2 (en) * 2015-11-24 2020-03-31 General Electric Company Engine component with film cooling
DE102018209610A1 (de) * 2018-06-14 2019-12-19 MTU Aero Engines AG Schaufelblatt für eine Strömungsmaschine
CN109139545B (zh) * 2018-11-14 2024-05-03 珠海格力电器股份有限公司 叶片、贯流风叶及空调器
IT202100000296A1 (it) 2021-01-08 2022-07-08 Gen Electric Motore a turbine con paletta avente un insieme di fossette

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5577555A (en) * 1993-02-24 1996-11-26 Hitachi, Ltd. Heat exchanger
US5975850A (en) * 1996-12-23 1999-11-02 General Electric Company Turbulated cooling passages for turbine blades
WO1999064791A1 (en) * 1998-06-08 1999-12-16 Solar Turbines Incorporated Combustor cooling method
EP1065345A2 (de) * 1999-06-30 2001-01-03 General Electric Company Turbinenelement mit erhöhter Wärmeleitfähigkeit und dessen Herstellungsweise
EP1116537A2 (de) * 2000-01-10 2001-07-18 General Electric Company Gussstück mit verbesserter Wärmeübertragungsfläche, sowie Giessform und Modell zu ihrer Herstellung
WO2001071164A1 (de) * 2000-03-22 2001-09-27 Siemens Aktiengesellschaft Versteifungs- und kühlstruktur einer turbinenschaufel
US6644921B2 (en) * 2001-11-08 2003-11-11 General Electric Company Cooling passages and methods of fabrication
US20040052643A1 (en) * 2002-09-18 2004-03-18 Bunker Ronald Scott Linear surface concavity enhancement

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4142824A (en) * 1977-09-02 1979-03-06 General Electric Company Tip cooling for turbine blades
US5413463A (en) * 1991-12-30 1995-05-09 General Electric Company Turbulated cooling passages in gas turbine buckets
EP1022435B1 (de) * 1999-01-25 2009-06-03 General Electric Company Interner Kühlkreislauf für eine Gasturbinenschaufel
US6142734A (en) * 1999-04-06 2000-11-07 General Electric Company Internally grooved turbine wall
US6504274B2 (en) * 2001-01-04 2003-01-07 General Electric Company Generator stator cooling design with concavity surfaces
US7302990B2 (en) * 2004-05-06 2007-12-04 General Electric Company Method of forming concavities in the surface of a metal component, and related processes and articles

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5577555A (en) * 1993-02-24 1996-11-26 Hitachi, Ltd. Heat exchanger
US5975850A (en) * 1996-12-23 1999-11-02 General Electric Company Turbulated cooling passages for turbine blades
WO1999064791A1 (en) * 1998-06-08 1999-12-16 Solar Turbines Incorporated Combustor cooling method
EP1065345A2 (de) * 1999-06-30 2001-01-03 General Electric Company Turbinenelement mit erhöhter Wärmeleitfähigkeit und dessen Herstellungsweise
EP1116537A2 (de) * 2000-01-10 2001-07-18 General Electric Company Gussstück mit verbesserter Wärmeübertragungsfläche, sowie Giessform und Modell zu ihrer Herstellung
WO2001071164A1 (de) * 2000-03-22 2001-09-27 Siemens Aktiengesellschaft Versteifungs- und kühlstruktur einer turbinenschaufel
US6644921B2 (en) * 2001-11-08 2003-11-11 General Electric Company Cooling passages and methods of fabrication
US20040052643A1 (en) * 2002-09-18 2004-03-18 Bunker Ronald Scott Linear surface concavity enhancement

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3052990A1 (fr) * 2016-06-28 2017-12-29 Snecma Circuit de refroidissement d'une aube de turbomachine
WO2018002466A1 (fr) 2016-06-28 2018-01-04 Safran Aircraft Engines Circuit de refroidissement d'une aube de turbomachine
US10682687B2 (en) 2016-06-28 2020-06-16 Safran Aircraft Engines Turbomachine blade cooling circuit
EP4092249A1 (de) * 2021-05-19 2022-11-23 Rolls-Royce plc Düsenleitschaufel
US11634994B2 (en) 2021-05-19 2023-04-25 Rolls-Royce Plc Nozzle guide vane

Also Published As

Publication number Publication date
US20050260076A1 (en) 2005-11-24
UA86580C2 (ru) 2009-05-12
EP1598523B1 (de) 2016-01-20
RU2388915C2 (ru) 2010-05-10
RU2005114173A (ru) 2006-11-20
US7513737B2 (en) 2009-04-07
CA2504168A1 (fr) 2005-11-18
FR2870560A1 (fr) 2005-11-25
JP2005330966A (ja) 2005-12-02
FR2870560B1 (fr) 2006-08-25
CA2504168C (fr) 2012-12-18
JP4854985B2 (ja) 2012-01-18

Similar Documents

Publication Publication Date Title
CA2504168C (fr) Circuit de refroidissement a cavite a rapport de forme eleve pour aube de turbine a gaz
EP1741875B1 (de) Kühlkreislauf für eine Rotorschaufel einer Turbomaschine
EP1726783B1 (de) Hohle Laufschaufel für die Turbine eines Gasturbinentriebwerks, mit einem Hohlraum
EP2705223B1 (de) Vorrichtung zum abdichten eines strömungskanals von einer turbine einer strömungsmaschine
EP2352922B1 (de) Schaufeln mit öffnungen aufweisender diffuser
FR2875262A1 (fr) Procedes et dispositifs pour assembler des ensembles de rotors de moteurs a turbines a gaz
FR2914943A1 (fr) Aube de soufflante
EP2694781B1 (de) Dichtring für eine turbinenstufe einer flugzeugturbomaschine mit geschlitzten drehschutzzapfen
EP1333155A1 (de) Kühlung der Abströmkante einer Hochdruckturbinenlaufschaufel
EP1630351B1 (de) Schaufel eines Verdichters oder einer Gasturbine
EP1318274B1 (de) Hochdruck-Turbinenschaufel mit gekühlter Abströmkante
FR3029242A1 (fr) Aube de turbomachine, comprenant des cloisons entrecroisees pour la circulation d'air en direction du bord de fuite
FR3108363A1 (fr) Aube de turbine comportant trois types d’orifices de refroidissement du bord de fuite
EP3420198A1 (de) Gleichrichter für turbomaschinenverdichter eines flugzeugs mit luftabsaugungsöffnungen mit gestreckter form im umfangsrichtung
WO2021245339A1 (fr) Distributeur de turbine pour une turbomachine
WO2020193913A1 (fr) Aube de turbomachine equipee d'un circuit de refroidissement optimise
FR3100836A1 (fr) Aubes mobiles pour turbine
WO2023156726A1 (fr) Assemblage pour une turbomachine d'aéronef et turbomachine d'aéronef
FR3127018A1 (fr) Aube mobile pour turbine de turbomachine, présentant une conception améliorant l’étanchéité des cavités inter-aubes
WO2021019156A1 (fr) Aube mobile de turbomachine a circuit de refroidissement ayant une double rangee de fentes d'evacuation
FR3111661A1 (fr) Aube de turbine avec système de refroidissement
FR3116857A1 (fr) composant de turbomachine comprenant une paroi pourvue de moyens de refroidissement
EP3942157A1 (de) Turbinenmotorschaufel mit kühlkreislauf und wachsausschmelzverfahren zur herstellung einer solchen schaufel
FR3127255A1 (fr) Ensemble rotatif pour turbomachine
EP3797009A1 (de) Rauguss-beschaufelung mit modifizierter hinterkantengeometrie

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: 20050425

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid

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

17Q First examination report despatched

Effective date: 20061128

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150715

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: DE

Ref legal event code: R096

Ref document number: 602005048327

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160120

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602005048327

Country of ref document: DE

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: 20161021

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

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

Ref country code: GB

Payment date: 20240320

Year of fee payment: 20

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

Ref country code: SE

Payment date: 20240320

Year of fee payment: 20

Ref country code: IT

Payment date: 20240320

Year of fee payment: 20

Ref country code: FR

Payment date: 20240320

Year of fee payment: 20

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

Ref country code: DE

Payment date: 20240320

Year of fee payment: 20