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EP0851095B1 - Aube de turbomachine avec refroidissement interieur - Google Patents

Aube de turbomachine avec refroidissement interieur Download PDF

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Publication number
EP0851095B1
EP0851095B1 EP97810917A EP97810917A EP0851095B1 EP 0851095 B1 EP0851095 B1 EP 0851095B1 EP 97810917 A EP97810917 A EP 97810917A EP 97810917 A EP97810917 A EP 97810917A EP 0851095 B1 EP0851095 B1 EP 0851095B1
Authority
EP
European Patent Office
Prior art keywords
pins
wall
coolant
turbomachine blade
narrow gap
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
EP97810917A
Other languages
German (de)
English (en)
Other versions
EP0851095A1 (fr
Inventor
Kenneth Hall
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom 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 Alstom SA filed Critical Alstom SA
Publication of EP0851095A1 publication Critical patent/EP0851095A1/fr
Application granted granted Critical
Publication of EP0851095B1 publication Critical patent/EP0851095B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
    • F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
    • F28F1/124—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and being formed of pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • F28F3/022—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being wires or pins
    • 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

Definitions

  • the invention relates to an internally cooled turbomachine blade, with a Wall (W), which on the outside of a hot medium and on your A coolant flows around the inner wall, as well as with, in the inner wall introduced thermal bridges in the form of high-melting pins (S) with high thermal conductivity in the space exposed to the coolant (E) protrude.
  • W Wall
  • S high-melting pins
  • Such internally cooled turbomachine blades are for example those of gas turbines with axial flow.
  • Hollow, internally cooled turbine blades with liquid, steam or air as Coolants are well known.
  • a particular problem is the cooling of the The trailing edge of such blades represents that in a closed circle of the coolant are flowed through.
  • the walls forming the rear edge include one Narrow gap from which the heat is to be removed.
  • the narrow gap in its Width should not be less than a minimum value.
  • the wall thickness may be a certain one for reasons of strength Do not fall short.
  • the invention has for its object an internally cooled Turbomachine blade to develop such that the known Overheating problems on the rear edge of the turbine blade reduced or completely should be avoided without losing the fluid mechanical properties to influence the rear edge sustainably.
  • the narrow gap that the trailing edge encloses can be improved.
  • an internally cooled turbomachine blade with a wall which is surrounded by a hot medium on its outside and a coolant on its inside wall, and with thermal bridges introduced in the inside wall in the form of high-melting pins with high thermal conductivity, which in the from Project coolant-loaded space, developed such that the coolant-charged space is a closed narrow gap, which is formed by the rear edge of the turbomachine blade from which the pins protrude into the narrow gap, and that the wall at the rear edge encloses the melting pins with a constant wall thickness.
  • the advantages of the invention include the simplicity of the measure see. If the wall to be cooled is a cast one Turbine blade, so the pins can be shed together with the blade become. The measure also allows the efficiency of the training Blade trailing edge.
  • the cast blade shown in FIG. 1 has three inner chambers a, b, and c, through which a coolant, for example steam, flows, perpendicular to the plane of the drawing.
  • a coolant for example steam
  • the inside of the wall W forming the blade contour - which is surrounded by hot gases on the outside on both sides - is surrounded by the coolant and gives off its heat to the coolant.
  • the coolant circulates in a closed circuit, which means that coolant is not blown out into the flow channel either on the front edge, the suction side, the pressure side or in the region of the rear edge. This results in the problem with the trailing edge geometry, which is explained with reference to FIG. 2.
  • the narrow gap E formed by the walls must have a minimum size in order to be able to absorb enough coolant to dissipate the heat generated.
  • the inner edge rounding must therefore be designed with the diameter d.
  • a minimum wall thickness T cannot be undershot.
  • the dimension L a therefore generally corresponds to the wall thickness T. All this means that the outer edge rounding must be carried out with a relatively large diameter D a . So far, cooled trailing edges are known.
  • the invention seeks to remedy this. 3 are for better Heat dissipation in the wall around which the coolant flows Form of pins S arranged. These pins are attached so that they are in the from Coolant-loaded space, i.e. protrude into the narrow gap E.
  • the thermal bridges are high-melting material. Because such internally cooled blades usually are cast, it is advisable to arrange the pins in the casting cores beforehand and integrally potting them with the shovel. This has the advantage that in this Area on the usual spacers in the form of quartz or aluminide struts can be dispensed with.
  • pins are high Thermal conductivity to choose.
  • This is a suitable material synthetic diamond.
  • a synthetic diamond made of C-14 isotopes has shown thermal conductivity.
  • the pins S are cylindrical. It goes without saying that too other geometries with larger exchange areas are possible, for example, pins that have a polygonal shape in cross section or are serrated are.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Geometry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (4)

  1. Aube de turbomachine avec refroidissement intérieur, comprenant une paroi (W) qui est parcourue sur son côté extérieur par un fluide chaud et sur sa paroi intérieure par un fluide de refroidissement, et comprenant aussi des ponts thermiques réalisés dans la paroi intérieure, en forme de tiges (S) à haut point de fusion et à haute conductibilité thermique, qui pénètrent dans l'espace (E) sollicité par le fluide de refroidissement, caractérisée en ce que l'espace (E) sollicité par le fluide de refroidissement est une fente étroite fermée (E), qui est formée par le bord arrière de l'aube de turbomachine, depuis lequel les tiges (S) pénètrent dans la fente étroite, et en ce que la paroi (W) au niveau du bord arrière entoure avec une épaisseur de paroi (T) inchangée les tiges (S) à haut point de fusion.
  2. Aube de turbomachine avec refroidissement intérieur selon la revendication 1, caractérisée en ce que les tiges (S) se composent de diamant synthétique en isotopes du C-14.
  3. Aube de turbomachine avec refroidissement intérieur selon la revendication 1, caractérisée en ce que les tiges (S) sont coulées conjointement avec la paroi (W).
  4. Aube de turbomachine avec refroidissement intérieur selon la revendication 1, caractérisée en ce que la fente étroite (E) s'étend au moins approximativement sur toute la hauteur de l'aube de turbomachine, et qu'une pluralité de tiges sont réparties sur la hauteur.
EP97810917A 1996-12-23 1997-11-27 Aube de turbomachine avec refroidissement interieur Expired - Lifetime EP0851095B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19654115A DE19654115A1 (de) 1996-12-23 1996-12-23 Vorrichtung zum Kühlen einer beidseitig umströmten Wand
DE19654115 1996-12-23

Publications (2)

Publication Number Publication Date
EP0851095A1 EP0851095A1 (fr) 1998-07-01
EP0851095B1 true EP0851095B1 (fr) 2002-09-25

Family

ID=7816083

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810917A Expired - Lifetime EP0851095B1 (fr) 1996-12-23 1997-11-27 Aube de turbomachine avec refroidissement interieur

Country Status (4)

Country Link
EP (1) EP0851095B1 (fr)
JP (1) JPH10196304A (fr)
CN (1) CN1186151A (fr)
DE (2) DE19654115A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1046784B1 (fr) 1999-04-21 2004-08-11 ALSTOM Technology Ltd Structure refroidie
DE19926817A1 (de) * 1999-06-12 2000-12-14 Abb Research Ltd Turbinenbauteil
GB0008897D0 (en) * 2000-04-12 2000-05-31 Cheiros Technology Ltd Improvements relating to heat transfer
US11333022B2 (en) * 2019-08-06 2022-05-17 General Electric Company Airfoil with thermally conductive pins

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE559676C (de) * 1931-08-20 1932-09-22 E H Hans Holzwarth Dr Ing Verfahren zur Kuehlung von Schaufeln, insbesondere fuer Brennkraftturbinen
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
DE3211139C1 (de) * 1982-03-26 1983-08-11 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke
GB8607526D0 (en) * 1986-03-26 1986-04-30 Artus R G C Cooled component assembly
US5810552A (en) * 1992-02-18 1998-09-22 Allison Engine Company, Inc. Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
FR2714254B1 (fr) * 1993-12-20 1996-03-08 Aerospatiale Elément de transfert thermique, utilisable notamment en électronique comme support de circuit imprimé ou de composant et son procédé de fabrication.
US5566752A (en) * 1994-10-20 1996-10-22 Lockheed Fort Worth Company High heat density transfer device
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket

Also Published As

Publication number Publication date
DE59708321D1 (de) 2002-10-31
JPH10196304A (ja) 1998-07-28
EP0851095A1 (fr) 1998-07-01
CN1186151A (zh) 1998-07-01
DE19654115A1 (de) 1998-06-25

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