EP0160291B1 - Ailette refroidie de turbine - Google Patents

Ailette refroidie de turbine Download PDF

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Publication number
EP0160291B1
EP0160291B1 EP85105185A EP85105185A EP0160291B1 EP 0160291 B1 EP0160291 B1 EP 0160291B1 EP 85105185 A EP85105185 A EP 85105185A EP 85105185 A EP85105185 A EP 85105185A EP 0160291 B1 EP0160291 B1 EP 0160291B1
Authority
EP
European Patent Office
Prior art keywords
mat
cooling
wiremesh
wire mesh
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.)
Expired
Application number
EP85105185A
Other languages
German (de)
English (en)
Other versions
EP0160291A1 (fr
Inventor
Karl-Heinz Dipl.-Ing. Collin
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.)
CESSIONE;KHD LUFTFAHRTTECHNIK GMBH
Original Assignee
Kloeckner Humboldt Deutz 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 Kloeckner Humboldt Deutz AG filed Critical Kloeckner Humboldt Deutz AG
Publication of EP0160291A1 publication Critical patent/EP0160291A1/fr
Application granted granted Critical
Publication of EP0160291B1 publication Critical patent/EP0160291B1/fr
Expired 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
    • 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
    • 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 invention relates to a turbine blade according to the preamble of claim 1.
  • Modern gas turbine engines require relatively high gas temperatures (turbine inlet temperatures) in order to achieve optimum working process efficiencies.
  • the components coming into contact with the aforementioned hot gases, e.g. B. the stator and impeller blades of the gas turbine engine are therefore exposed to considerable stress.
  • it is customary to cool the turbine blades inside with air in most applications is used as the coolant, which is preferably taken from a suitable point on the compressor of the gas turbine engine and passed through cooling ducts provided within the blades of the turbine blade (convection cooling).
  • a further possibility for improving the internal convection cooling is an optimized design or arrangement of the cooling channels in order to effectively reduce the blade temperature through improved utilization of the cooling air with the same cooling air mass flows.
  • the object of the invention is to optimize the cooling effect of the available cooling medium with the simplest possible means through an improved design and arrangement of the wire mesh mats.
  • the wire mesh mats can be a plurality of wire mesh mats arranged one behind the other in the flow direction of the cooling air within the throughflow space or the cooling channels, wherein individual wire mesh mats each extend to opposite wall regions of the cooling channels.
  • the wire mesh mats can be connected to one another or additionally in the flow direction of the cooling air, ie essentially in the longitudinal direction of the cooling channel or channels, and the cooling air channels
  • knobs or pins provided on individual wall areas.
  • the wire mesh mats can be wire meshes which are present as standard and have very small dimensions, both in terms of wire diameter and mesh size, in contrast to the cross-sectional dimensions of the flow-through space or the cooling channels, as described, for example, in FIG. B. can be found in conventional filter screens.
  • the individual wires of the wire mesh mat are soldered or welded to the respective regions of the boundary wall of the flow-through space or the cooling channels and also preferably at the crossing points.
  • a hard solder e.g. Degussa nickel hard solder 8100 with a soldering temperature of 1420 to 1470 ° K
  • the soldered connection of the folding areas to the boundary wall is preferably designed such that the wires extending in the longitudinal direction of the cooling channel are also covered by the thermally conductive soldered connection of the folding area, in order to also use the longitudinal wires for cooling and comparison at these points.
  • the manufacturing effort is greatly simplified despite the much more intensive use of the available cooling air, since the casting requirements for the turbine blade according to the invention (e.g. the elimination of special cores for the elements) are considerably reduced.
  • the wire mesh mat can be guided into an opening extending from the throughflow space to an outer surface and then connected to the boundary wall of the cooling channels by soldering or welding. Before folding the wire mesh mat, it is preferably in the. To provide folding areas with soldering or welding points, which on the one hand simplifies the folding and on the other hand also ensures that the wires running longitudinally in the flow direction can also be used for heat transfer.
  • the airfoil 1 of the turbine blade of a radial or axial turbine for gas turbine engines has cooling channels 2 through which cooling air taken from a suitable point of the compressor, not shown, of the gas turbine engine flows in the axial direction (arrows 2a).
  • the folded and intersecting elements 3 are arranged within the cooling channels 2 in order to enlarge the heat exchange surface.
  • the elements 3 are wires of a wire mesh mat 4 which, with a plurality of folding regions 5, extends essentially in a wave-like manner in the flow direction 2a of the cooling air.
  • the enlarged section A (FIG. 2) of the wire mesh mat 4 of the exemplary embodiment of the turbine blade according to FIG. 1 and the view in the flow direction 2 a corresponding to the section line III-III of FIG. 1 (FIG. 3) clarify the design and arrangement of the wire mesh mat 4 within of the cooling air ducts 2.
  • the wire mesh mat 4 extends in one piece essentially in a wave-like manner within the cooling ducts 2 and completely penetrates the cooling ducts transversely to the flow direction 2a of the cooling air 2.
  • the elements or wires 3 running transversely to the flow direction 2a of the cooling air are in each case for better heat conduction with the connected in a wave-like manner in the longitudinal direction of the cooling channels 2 longitudinal wires.
  • the wire mesh mat 4 is connected to opposite boundary walls 6 by a thermally conductive solder connection 9.
  • the wire mesh mat 4 is designed in an analogous manner to that in the exemplary embodiment according to FIG. 1 with a wave-like course in the flow direction of the cooling air, in this exemplary embodiment the wire mesh mat 4 extending over the entire length of the essentially radially directed one Cooling air duct of the turbine blade (flow chamber 10) extends.

Claims (3)

1. Ailette de turbine d'un mécanisme de turbine à gaz, présentant dans ses pales d'ailette (1) au moins un canal de refroidissement (2), formé pour un moyen de refroidissement en tant qu'espace (10) traversé par le flux, dans laquelle, à l'intérieur de l'espace (10) traversé par le flux sont prévus des éléments (3) formés d'au moins un tissu de toile métallique (4), pour l'augmentation de la surface d'échange thermique, dans laquelle les éléments (3) pour l'augmentation de la surface d'échange thermique sont croisés les uns avec les autres, et sont liés à leurs endroits de croisement les uns avec les autres par une liaison conductrice de la chaleur, et s'étendent jusqu'aux différentes régions des parois (6) de l'espace (10) traversé par le flux, caractérisée en ce que le tissu de toile métallique (4) s'étend dans la direction (2a) du flux du moyen de refroidissement, de façon continue, plusieurs fois plié et essentiellement sous forme ondulée, dans laquelle les régions de pliage (5) sont reliées aux parois (6) par une liaison conductrice de la chaleur, et en ce que les surfaces du tissu de toile métallique (4) se trouvant entre les régions de pliage (5) sont traversées par le flux du moyen de refroidissement.
2. Ailette de turbine selon la revendication 1, caractérisée en ce que les régions de pliage (5) du tissu de toile métallique (4) sont brasées ou soudées avec la paroi de limitation (6) de l'espace (10) traversé par le flux ou des canaux de refroidissement -(2).
3. Ailette de turbine selon les revendications 1 ou 2, caractérisée en ce que les pales d'ailette présentent une ouverture s'étendant depuis l'espace (10) traversé par le flux jusqu'à une surface extérieure, pour l'introduction du tissu de toile métallique (4), lequel est brasé après sa mise en place.
EP85105185A 1984-04-30 1985-04-28 Ailette refroidie de turbine Expired EP0160291B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843416087 DE3416087A1 (de) 1984-04-30 1984-04-30 Gekuehlte turbinenschaufel
DE3416087 1984-04-30

Publications (2)

Publication Number Publication Date
EP0160291A1 EP0160291A1 (fr) 1985-11-06
EP0160291B1 true EP0160291B1 (fr) 1988-05-25

Family

ID=6234722

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85105185A Expired EP0160291B1 (fr) 1984-04-30 1985-04-28 Ailette refroidie de turbine

Country Status (2)

Country Link
EP (1) EP0160291B1 (fr)
DE (2) DE3416087A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2678318B1 (fr) * 1991-06-25 1993-09-10 Snecma Aube refroidie de distributeur de turbine.
RU2151303C1 (ru) * 1996-03-14 2000-06-20 АББ Унитурбо Лтд. Охлаждаемая рабочая или сопловая лопатка газовой турбины
EP1495079A1 (fr) 2001-12-19 2005-01-12 Clariant Finance (BVI) Limited Colorants monoazoiques acides
EP2025868A1 (fr) * 2007-08-10 2009-02-18 Siemens Aktiengesellschaft Aube de turbine avec turbulateur à l'entrée d'air de refroidissement
FR3035640B1 (fr) * 2015-04-29 2017-05-05 Snecma Aube de stator a calage variable, comprenant des cloisons transversales entrecroisees
CN112145236B (zh) * 2020-09-24 2021-11-05 大连理工大学 一种双s型回转腔层板冷却结构

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE485284A (fr) * 1947-10-28
NL73916C (fr) * 1949-07-06 1900-01-01
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
GB774499A (en) * 1953-06-19 1957-05-08 Power Jets Res & Dev Ltd Corrugated-cored elements for use in turbines, compressors and combustion equipment
US2888241A (en) * 1954-06-09 1959-05-26 Stalker Corp Fabricated cooled turbine blades
US3627444A (en) * 1969-11-24 1971-12-14 Gen Motors Corp Wick lined vanes and their manufacture
FR2483513A1 (fr) * 1980-05-28 1981-12-04 Snecma Procede pour la fabrication d'aubes de turbine refroidies au moyen d'un corps poreux et produit obtenu suivant ce procede

Also Published As

Publication number Publication date
DE3562939D1 (en) 1988-06-30
EP0160291A1 (fr) 1985-11-06
DE3416087A1 (de) 1985-10-31

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