EP2022939A1 - Elément de refroidissement de projection et composant pour gaz chaud doté d'un élément de refroidissement de projection - Google Patents

Elément de refroidissement de projection et composant pour gaz chaud doté d'un élément de refroidissement de projection Download PDF

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Publication number
EP2022939A1
EP2022939A1 EP07015384A EP07015384A EP2022939A1 EP 2022939 A1 EP2022939 A1 EP 2022939A1 EP 07015384 A EP07015384 A EP 07015384A EP 07015384 A EP07015384 A EP 07015384A EP 2022939 A1 EP2022939 A1 EP 2022939A1
Authority
EP
European Patent Office
Prior art keywords
cooling element
impingement cooling
hot gas
gas component
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Withdrawn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
EP07015384A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Hans-Thomas Dr. Bolms
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 EP07015384A priority Critical patent/EP2022939A1/fr
Publication of EP2022939A1 publication Critical patent/EP2022939A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the impingement cooling element 28 is essentially ceramic. That is, the impingement cooling member 28 has a ceramic as a main component. It is therefore not a metallic impingement cooling element with a ceramic coating. If necessary, the ceramic can also have stiffening elements such as fibers or similar structures.
  • the impingement cooling element 28 inserted into the cavity 24 is located at a distance from the blade wall 20, 22 to be cooled. Thus, between the blade wall 20, 22 to be cooled and the impingement cooling element 28, a gap 30 is provided, through which the coolant flowing inside the ceramic is provided by means provided in the impingement cooling element 28 Openings 32 can radiate out.
  • the coolant flowing out of the impingement cooling openings 32 impinges substantially perpendicularly on the inside of the wall 20, 22 of the turbine guide vane to be cooled.
  • the wall 20, 22 is cooled in a known manner. Subsequently, the coolant present in the intermediate space 30 can flow out of this.
  • the ceramic is formed as a porous ceramic, so that the porosity makes it possible to form the cooling air jets impinging on the wall 20, 22 to be cooled.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07015384A 2007-08-06 2007-08-06 Elément de refroidissement de projection et composant pour gaz chaud doté d'un élément de refroidissement de projection Withdrawn EP2022939A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07015384A EP2022939A1 (fr) 2007-08-06 2007-08-06 Elément de refroidissement de projection et composant pour gaz chaud doté d'un élément de refroidissement de projection

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07015384A EP2022939A1 (fr) 2007-08-06 2007-08-06 Elément de refroidissement de projection et composant pour gaz chaud doté d'un élément de refroidissement de projection

Publications (1)

Publication Number Publication Date
EP2022939A1 true EP2022939A1 (fr) 2009-02-11

Family

ID=39591587

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07015384A Withdrawn EP2022939A1 (fr) 2007-08-06 2007-08-06 Elément de refroidissement de projection et composant pour gaz chaud doté d'un élément de refroidissement de projection

Country Status (1)

Country Link
EP (1) EP2022939A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1163970A1 (fr) * 2000-06-16 2001-12-19 General Electric Company Méthode pour former des orifices dans des composants de turbine réalisés en matériau composite à matrice céramique
EP1284338A2 (fr) * 2001-08-13 2003-02-19 General Electric Company Insert avec sortie tangentielle de fluide de refroidissement
EP1801502A2 (fr) * 2005-12-22 2007-06-27 United Technologies Corporation Chemise de chambre de combustion à double paroi

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1163970A1 (fr) * 2000-06-16 2001-12-19 General Electric Company Méthode pour former des orifices dans des composants de turbine réalisés en matériau composite à matrice céramique
EP1284338A2 (fr) * 2001-08-13 2003-02-19 General Electric Company Insert avec sortie tangentielle de fluide de refroidissement
EP1801502A2 (fr) * 2005-12-22 2007-06-27 United Technologies Corporation Chemise de chambre de combustion à double paroi

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