EP1457641A1 - Procédé de refroidissement d'un composant pour guider des gaz chauds et composant à refroidir - Google Patents

Procédé de refroidissement d'un composant pour guider des gaz chauds et composant à refroidir Download PDF

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Publication number
EP1457641A1
EP1457641A1 EP03005535A EP03005535A EP1457641A1 EP 1457641 A1 EP1457641 A1 EP 1457641A1 EP 03005535 A EP03005535 A EP 03005535A EP 03005535 A EP03005535 A EP 03005535A EP 1457641 A1 EP1457641 A1 EP 1457641A1
Authority
EP
European Patent Office
Prior art keywords
component
cooling
layer
cooled
wall
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.)
Withdrawn
Application number
EP03005535A
Other languages
German (de)
English (en)
Inventor
Beate Seiler
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 EP03005535A priority Critical patent/EP1457641A1/fr
Publication of EP1457641A1 publication Critical patent/EP1457641A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • F05D2300/141—Silver
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/172—Copper alloys
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5024—Heat conductivity

Definitions

  • the invention relates to a method for cooling a hot gas-carrying component and a component to be cooled the preamble of claims 1 and 2.
  • Components in gas turbines are often high thermal Exposed to stress. These components then get on the "hot" side, for example, an outer ceramic Thermal barrier and / or are on the side that the opposite hot side, cooled by impingement cooling to reduce the thermal loads.
  • the object is achieved by a method for cooling a hot gas-carrying component and a component to be cooled Claims 1 and 2.
  • Component with which the inventive method is carried out can be.
  • Figure 1 shows a component according to the prior art a wall 2, the outside 4 ("hot" side) and one Has inside 13.
  • a hot gas for example a gas turbine, flows along the outside 4 in a flow direction 7, for example in a hot runner 28. Without impingement cooling, the temperature in flow direction 7 would be approximately the same at a certain depth in wall 2 (ie in radial direction 31, that is perpendicular to flow direction 7); In the radial direction 31 there would be a temperature gradient in the wall 2 which is the same along the flow direction 7.
  • a cooling medium 10 air, steam, ..
  • the medium 10 which is used for impingement cooling, only partially strikes the inside 13 at impact points 18, so that the temperature at the impact points 18 and at regions 16 which adjoin the impact points 18 in the wall 2 is significantly lower than in areas 17 where the cooling medium does not strike.
  • the temperature distribution in the wall 2 in the flow direction 7 at a certain depth in the wall 2 ie in the radial direction 31
  • the gradient is very different depending on the position in the flow direction 7, ie depending on whether it runs through the area 16 or 17.
  • thermomechanical loads on the wall 2 leads to a can lead to early component failure.
  • FIG. 2 shows a component 1 according to the invention, with which the The inventive method can be carried out.
  • the component 1 is, for example, a hollow component 1, for example a turbine blade, combustion chamber lining, or the like, which is cooled on the inside.
  • the component 1 consists for example of a nickel or cobalt-based super alloy.
  • the inside 13 delimits a cavity (not shown).
  • a layer 19 is applied on the inside 13, which has a significantly higher coefficient of thermal conductivity than the material of the component 1 or the wall 2, in particular higher than in the vicinity of the inside 13.
  • the coefficient of thermal conductivity of the layer 19 is at least 10% greater than that Thermal conductivity coefficient of the wall 2, but preferably also 20%, 50%, 100% or more. Copper, silver or alloys can be used as the material for the layer 19. Other materials with very good thermal conductivity are also possible.
  • the layer 19 can also be applied to a layer already present on a base material.
  • the cooling medium 10 for impingement cooling now meets this Layer 19 on. Since the layer 19 is a very good heat conductor Layer, it distributes the heat, so not like in Figure 1 several discrete zones 16 with significantly reduced Temperature arise, but that on the inside 13 a continuous area 22 along the flow direction 7 arises, which is approximately the same in the radial direction 31 Has temperature gradients. The heat is thus removed very evenly, so that thermomechanical loads be reduced.
  • the cooling capacity is also increased.
  • a baffle cooling plate (not shown), which is arranged at a certain distance from the inside 13, is also used for the baffle cooling.
  • the cooling medium flows through the baffle cooling plate and then strikes the heat-conducting layer 19.
  • FIG. 3 shows a further component 1 according to the invention, with which the method according to the invention can be carried out.
  • component 1 also has a cooling air hole 25 through which the cooling medium 10 flows after the impingement cooling has taken place in the hot gas duct 28 and there contributes to film cooling of the component 1 on the outside 4 in the outside space.
  • the cooling air hole 25 passes through the layer 19 and can also have a highly heat-conducting layer.
EP03005535A 2003-03-11 2003-03-11 Procédé de refroidissement d'un composant pour guider des gaz chauds et composant à refroidir Withdrawn EP1457641A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03005535A EP1457641A1 (fr) 2003-03-11 2003-03-11 Procédé de refroidissement d'un composant pour guider des gaz chauds et composant à refroidir

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03005535A EP1457641A1 (fr) 2003-03-11 2003-03-11 Procédé de refroidissement d'un composant pour guider des gaz chauds et composant à refroidir

Publications (1)

Publication Number Publication Date
EP1457641A1 true EP1457641A1 (fr) 2004-09-15

Family

ID=32748859

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03005535A Withdrawn EP1457641A1 (fr) 2003-03-11 2003-03-11 Procédé de refroidissement d'un composant pour guider des gaz chauds et composant à refroidir

Country Status (1)

Country Link
EP (1) EP1457641A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4368697A (en) * 1980-03-05 1983-01-18 Karl Schmidt Gmbh Liquid-cooled piston for internal combustion engines
GB2111604A (en) * 1981-12-09 1983-07-06 Westinghouse Electric Corp Shell spar cooled airfoil using multiple spar cavities
US5533864A (en) * 1993-11-22 1996-07-09 Kabushiki Kaisha Toshiba Turbine cooling blade having inner hollow structure with improved cooling
US5738491A (en) * 1997-01-03 1998-04-14 General Electric Company Conduction blade tip
US5749229A (en) * 1995-10-13 1998-05-12 General Electric Company Thermal spreading combustor liner
EP1146201A2 (fr) * 2000-04-11 2001-10-17 General Electric Company Méthode d'adaptation d'épaisseur des parois laterales des segments des tuyères de guidage des turbines pour améliorer leur refroidissement
US6514046B1 (en) * 2000-09-29 2003-02-04 Siemens Westinghouse Power Corporation Ceramic composite vane with metallic substructure

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4368697A (en) * 1980-03-05 1983-01-18 Karl Schmidt Gmbh Liquid-cooled piston for internal combustion engines
GB2111604A (en) * 1981-12-09 1983-07-06 Westinghouse Electric Corp Shell spar cooled airfoil using multiple spar cavities
US5533864A (en) * 1993-11-22 1996-07-09 Kabushiki Kaisha Toshiba Turbine cooling blade having inner hollow structure with improved cooling
US5749229A (en) * 1995-10-13 1998-05-12 General Electric Company Thermal spreading combustor liner
US5738491A (en) * 1997-01-03 1998-04-14 General Electric Company Conduction blade tip
EP1146201A2 (fr) * 2000-04-11 2001-10-17 General Electric Company Méthode d'adaptation d'épaisseur des parois laterales des segments des tuyères de guidage des turbines pour améliorer leur refroidissement
US6514046B1 (en) * 2000-09-29 2003-02-04 Siemens Westinghouse Power Corporation Ceramic composite vane with metallic substructure

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Section PQ Week 197832, Derwent World Patents Index; Class Q51, AN 1978-G2534A, XP002250575 *

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