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EP0851095A1 - Dispositif de refroidissement pour une paroi - Google Patents

Dispositif de refroidissement pour une paroi Download PDF

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Publication number
EP0851095A1
EP0851095A1 EP97810917A EP97810917A EP0851095A1 EP 0851095 A1 EP0851095 A1 EP 0851095A1 EP 97810917 A EP97810917 A EP 97810917A EP 97810917 A EP97810917 A EP 97810917A EP 0851095 A1 EP0851095 A1 EP 0851095A1
Authority
EP
European Patent Office
Prior art keywords
wall
coolant
pins
narrow gap
cooled
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
EP97810917A
Other languages
German (de)
English (en)
Other versions
EP0851095B1 (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
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
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 a device for cooling a Wall, which is on the outside of a hot medium and a coolant flows around its inner wall.
  • Such walls to be cooled are, for example, the internally cooled ones Turbomachinery blades, especially those from axial flow gas turbines.
  • Hollow, internally cooled turbine blades with liquid, steam or air as a coolant are well known.
  • a problem provides in particular the cooling of the rear edge of such blades, which are in a closed circle from the coolant are flowed through.
  • the walls forming the rear edge include a narrow gap from which the heat is to be removed.
  • the narrow gap may have a minimal width Do not fall below the value.
  • To overheat the rear edge avoiding large amounts of material to be available.
  • the wall thickness is allowed For reasons of strength, do not fall below a certain level.
  • the invention has for its object on a cooled Wall to create a device that dissipates heat especially improved from a narrow gap.
  • the advantages of the invention include simplicity to see the measure. Is it the one to be cooled? Wall around a cast turbine blade, so the Pins are shed together with the shovel. The measure also allows an efficient training of Blade trailing edge.
  • the cast blade shown in Fig. 1 has three Inner chambers a, b, and c, which are surrounded by a coolant, for example steam, flows perpendicular to the plane of the drawing are. In doing so, the inside of the blade contour forming wall W - the outside on both sides of hot Gases flows around - flows around the coolant and give their Heat to the coolant. It is understood that at least numerous, not shown, in the two front chambers a, b Aids such as guide ribs, flow channels, inserts for Impingement cooling and the like to improve wall cooling can be provided.
  • the coolant circulates in a closed circle, which means that neither on the front edge, the suction side, the pressure side nor blowing out coolant in the area of the rear edge the flow channel takes place.
  • the gap E formed by the walls must have a minimum size in order to be able to absorb sufficient 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 of 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 used for better heat dissipation in the coolant flowed around the wall thermal bridges in the form of pins S arranged. These pins are attached so that they fit into the space exposed to the coolant, i.e. in the narrow gap E protrude into it.
  • Pins are used to ensure the desired heat dissipation to choose with high thermal conductivity.
  • This offers itself synthetic diamond as a suitable material.
  • a synthetic diamond from C-14 isotopes has been shown.
  • the pins S are cylindrical. It it goes without saying that other geometries, the larger exchange areas have, are possible, for example pens, which have a polygonal shape or toothed in cross section 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)
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
DE19654115 1996-12-23
DE19654115A DE19654115A1 (de) 1996-12-23 1996-12-23 Vorrichtung zum Kühlen einer beidseitig umströmten Wand

Publications (2)

Publication Number Publication Date
EP0851095A1 true EP0851095A1 (fr) 1998-07-01
EP0851095B1 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
EP1445423B1 (fr) * 1999-04-21 2006-08-02 Alstom Technology Ltd Aube de turbomachine 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

Citations (7)

* 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
DE3211139C1 (de) * 1982-03-26 1983-08-11 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke
EP0239322A2 (fr) * 1986-03-26 1987-09-30 Raymonde Gene Clifford Artus Ensemble à composants refroidis
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
EP0660400A1 (fr) * 1993-12-20 1995-06-28 AEROSPATIALE Société Nationale Industrielle 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
EP0750957A1 (fr) * 1995-06-07 1997-01-02 Allison Engine Company, Inc. Structures coulées en une seule pièce, à paroi mince avec une résistance à chaud élevée ou les parois sont interconnectées avec des éléments qui ont une conductivité thermique plus élevée

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket

Patent Citations (7)

* 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
DE3211139C1 (de) * 1982-03-26 1983-08-11 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Axialturbinenschaufel,insbesondere Axialturbinenlaufschaufel fuer Gasturbinentriebwerke
EP0239322A2 (fr) * 1986-03-26 1987-09-30 Raymonde Gene Clifford Artus Ensemble à composants refroidis
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
EP0660400A1 (fr) * 1993-12-20 1995-06-28 AEROSPATIALE Société Nationale Industrielle 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
EP0750957A1 (fr) * 1995-06-07 1997-01-02 Allison Engine Company, Inc. Structures coulées en une seule pièce, à paroi mince avec une résistance à chaud élevée ou les parois sont interconnectées avec des éléments qui ont une conductivité thermique plus élevée

Also Published As

Publication number Publication date
CN1186151A (zh) 1998-07-01
DE19654115A1 (de) 1998-06-25
DE59708321D1 (de) 2002-10-31
EP0851095B1 (fr) 2002-09-25
JPH10196304A (ja) 1998-07-28

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