EP1192333A1 - Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud - Google Patents

Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud

Info

Publication number
EP1192333A1
EP1192333A1 EP00942078A EP00942078A EP1192333A1 EP 1192333 A1 EP1192333 A1 EP 1192333A1 EP 00942078 A EP00942078 A EP 00942078A EP 00942078 A EP00942078 A EP 00942078A EP 1192333 A1 EP1192333 A1 EP 1192333A1
Authority
EP
European Patent Office
Prior art keywords
turbulators
wall
inclination
walls
turbine blade
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
EP00942078A
Other languages
German (de)
English (en)
Other versions
EP1192333B1 (fr
Inventor
Peter Tiemann
Michael Scheurlen
Dirk Anding
Hans-Thomas Bolms
Michael Strassberger
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP00942078A priority Critical patent/EP1192333B1/fr
Publication of EP1192333A1 publication Critical patent/EP1192333A1/fr
Application granted granted Critical
Publication of EP1192333B1 publication Critical patent/EP1192333B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the channel can be narrowed locally by the turbulators. This occurs in particular when the two opposite walls and thus the turbulators have different lengths. The turbulators of the two walls then face each other at the same height. The canal is narrowed locally at this point. As a rule, the wall is provided with several turbulators this narrowing occurs repeatedly. This does not result in a cooling fluid flow with a substantially constant cross-section which oscillates uniformly from one wall to the other wall. Rather, the cross-section available for the cooling fluid is constantly changed, so that pressure losses occur.
  • the object of the present invention is therefore to provide a component which can be subjected to hot gas and in which there is an essentially uniform channel cross section over the entire length of the turbulators without local constrictions.
  • the length of the first wall is advantageously greater than the length of the second wall. As a result, different cross-sections can be selected for the component which can be acted upon with gas.
  • Figure 5 is a section along the line V-V in Figure 2; 6 shows a section along the line VI-VI in Figure 2;
  • the two outer walls 16, 17 are curved and have a different length.
  • the outer wall 16 forms the suction side of the gas turbine blade 10
  • the outer wall 17 forms the pressure side.
  • the two partition walls 18, 19, which delimit the central channel 13, connect the outer walls 16, 17 to one another. These partitions 18, 19 are arranged at an angle to one another and are essentially perpendicular to the outer walls 16, 17. This achieves an optimization in the routing of the cooling fluid. Due to the angular position of the partition walls 18, 19 perpendicular to the outer walls 16, 17, loads on the gas turbine blade 10 that occur during operation can be better absorbed.
  • the turbulators 20 are also longer than the turbulators 21.
  • the turbulators 20 have the same angle of inclination with respect to the flow direction 22 of the Cooling fluids on like the turbulators 21 m in a projection parallel to one of the two walls 18, 19.
  • the turbulators 20, 21 can be opposed in sections at the same height.
  • FIG. 7 and FIG. 8 show a section along the line V-V and VI-VI in FIG. 2 in a gas turbine blade 10 according to the prior art.
  • the turbulators 20, 21 of the two outer walls 16, 17 are arranged alternately to one another on the left-hand side of the channel 13 in FIG. 2, which is shown in cross section in FIG.
  • the cooling fluid can flow uniformly from one outer wall 16 to the other in this area
  • the turbulators 20, 21 Due to the different inclination angles ⁇ , ⁇ , but the same direction of inclination of the turbulators 20, 21, the turbulators alternate almost completely. As shown in FIGS. 3 and 4, the turbulators 20, 21 do not lie opposite one another at any point. The cooling fluid can therefore swing freely from one outer wall 16 to the other outer wall 17. This applies both near the partition 18 and near the partition 19.
  • FIG. 10 For comparison, the mutual position of the turbulators 20, 21 in a gas turbine blade 10 according to the prior art is shown in FIG. 10 if the partition walls 18, 19 are not are parallel and the removal of the partitions 18 is carried out. It clearly shows that the turbulators 20, 21 are located opposite one another near the partition 19. The constriction 23 shown in FIG. 8 is thereby formed.

Landscapes

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

Abstract

La présent invention concerne un composant (10), notamment une aube de turbine, pouvant être exposé à un gaz chaud. Ce composant comprend au moins un canal (13) pouvant être alimenté en fluide de refroidissement et délimité par deux parois opposées (16, 17) dotées d'agitateurs (20, 21) de même sens d'inclinaison. Pour éviter les rétrécissements (23), les agitateurs (20) de la première paroi (16) ont, par rapport au sens d'écoulement (22) du fluide de refroidissement, un autre angle d'inclinaison (α) que celui des agitateurs (21) de la deuxième paroi (17).
EP00942078A 1999-06-28 2000-06-15 Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud Expired - Lifetime EP1192333B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP00942078A EP1192333B1 (fr) 1999-06-28 2000-06-15 Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP99112370 1999-06-28
EP99112370 1999-06-28
EP00942078A EP1192333B1 (fr) 1999-06-28 2000-06-15 Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud
PCT/EP2000/005525 WO2001000965A1 (fr) 1999-06-28 2000-06-15 Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud

Publications (2)

Publication Number Publication Date
EP1192333A1 true EP1192333A1 (fr) 2002-04-03
EP1192333B1 EP1192333B1 (fr) 2003-06-04

Family

ID=8238439

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00942078A Expired - Lifetime EP1192333B1 (fr) 1999-06-28 2000-06-15 Composant, notamment aube de turbine, pouvant etre expose a un gaz chaud

Country Status (5)

Country Link
US (1) US6641362B1 (fr)
EP (1) EP1192333B1 (fr)
JP (1) JP4489336B2 (fr)
DE (1) DE50002464D1 (fr)
WO (1) WO2001000965A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015073092A2 (fr) 2013-09-05 2015-05-21 United Technologies Corporation Générateur de tourbillon de surface portante de turbine à gaz pour résistance au fluage de surface portante

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7513745B2 (en) * 2006-03-24 2009-04-07 United Technologies Corporation Advanced turbulator arrangements for microcircuits
US7641445B1 (en) 2006-12-01 2010-01-05 Florida Turbine Technologies, Inc. Large tapered rotor blade with near wall cooling
US7866947B2 (en) * 2007-01-03 2011-01-11 United Technologies Corporation Turbine blade trip strip orientation
US7955053B1 (en) 2007-09-21 2011-06-07 Florida Turbine Technologies, Inc. Turbine blade with serpentine cooling circuit
US8376706B2 (en) * 2007-09-28 2013-02-19 General Electric Company Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method
US8042268B2 (en) * 2008-03-21 2011-10-25 Siemens Energy, Inc. Method of producing a turbine component with multiple interconnected layers of cooling channels
US20090324841A1 (en) * 2008-05-09 2009-12-31 Siemens Power Generation, Inc. Method of restoring near-wall cooled turbine components
EP2146055B2 (fr) † 2008-07-17 2022-01-19 Ansaldo Energia S.P.A. Élément d'étanchéité pour une turbine à gaz, turbine à gaz dotée dudit élément d'étanchéité et procédé de refroidissement dudit élément d'étanchéité
EP2602439A1 (fr) 2011-11-21 2013-06-12 Siemens Aktiengesellschaft Composant de gaz chaud pouvant être refroidi pour une turbine à gaz
EP2954168B1 (fr) * 2013-02-05 2019-07-03 United Technologies Corporation Pièce de turbine à gaz comportant un turbulateur incurvé
CN106481366B (zh) * 2015-08-28 2019-03-26 中国航发商用航空发动机有限责任公司 冷却叶片和燃气涡轮
US11085304B2 (en) 2018-06-07 2021-08-10 Raytheon Technologies Corporation Variably skewed trip strips in internally cooled components

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4627480A (en) * 1983-11-07 1986-12-09 General Electric Company Angled turbulence promoter
US5695322A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having restart turbulators
US5695321A (en) 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5681144A (en) * 1991-12-17 1997-10-28 General Electric Company Turbine blade having offset turbulators
US5700132A (en) * 1991-12-17 1997-12-23 General Electric Company Turbine blade having opposing wall turbulators
US5413458A (en) 1994-03-29 1995-05-09 United Technologies Corporation Turbine vane with a platform cavity having a double feed for cooling fluid
US5431537A (en) 1994-04-19 1995-07-11 United Technologies Corporation Cooled gas turbine blade
DE19634238A1 (de) 1996-08-23 1998-02-26 Asea Brown Boveri Kühlbare Schaufel
US5797726A (en) * 1997-01-03 1998-08-25 General Electric Company Turbulator configuration for cooling passages or rotor blade in a gas turbine engine
EP0892150B1 (fr) * 1997-07-14 2003-02-05 ALSTOM (Switzerland) Ltd Système de refroidissement pour le bord de fuite des aubes creuses d'une turbine à gaz

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0100965A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015073092A2 (fr) 2013-09-05 2015-05-21 United Technologies Corporation Générateur de tourbillon de surface portante de turbine à gaz pour résistance au fluage de surface portante

Also Published As

Publication number Publication date
DE50002464D1 (de) 2003-07-10
JP4489336B2 (ja) 2010-06-23
EP1192333B1 (fr) 2003-06-04
WO2001000965A1 (fr) 2001-01-04
US6641362B1 (en) 2003-11-04
JP2003503620A (ja) 2003-01-28

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