DE10337019A1 - Blade of gas turbine, comprising ceramic protection coating with partially polished areas for reduced heat generation - Google Patents

Blade of gas turbine, comprising ceramic protection coating with partially polished areas for reduced heat generation Download PDF

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Publication number
DE10337019A1
DE10337019A1 DE2003137019 DE10337019A DE10337019A1 DE 10337019 A1 DE10337019 A1 DE 10337019A1 DE 2003137019 DE2003137019 DE 2003137019 DE 10337019 A DE10337019 A DE 10337019A DE 10337019 A1 DE10337019 A1 DE 10337019A1
Authority
DE
Germany
Prior art keywords
blade
gas turbine
heat generation
protection coating
reduced heat
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Withdrawn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
DE2003137019
Other languages
German (de)
Inventor
Reinhard Fried
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 Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to DE2003137019 priority Critical patent/DE10337019A1/en
Publication of DE10337019A1 publication Critical patent/DE10337019A1/en
Withdrawn legal-status Critical Current

Links

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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The blade (1) of a turbine is protected by a ceramic thermal barrier coating (3) from the adverse effects of the hot gas (6) surrounding its outer surface (2). The level of roughness is reduced to a third of its previous condition in a first step by using an appropriate polishing method. At least one downstream area (7) is additionally polished in order to reduce the heat acting on the blade (1) even further. The particular position of the additionally polished areas (7) results in an increased efficacy because of the specific angle formed between the surface and the hot gas particles hitting the surface.
DE2003137019 2003-08-12 2003-08-12 Blade of gas turbine, comprising ceramic protection coating with partially polished areas for reduced heat generation Withdrawn DE10337019A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE2003137019 DE10337019A1 (en) 2003-08-12 2003-08-12 Blade of gas turbine, comprising ceramic protection coating with partially polished areas for reduced heat generation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2003137019 DE10337019A1 (en) 2003-08-12 2003-08-12 Blade of gas turbine, comprising ceramic protection coating with partially polished areas for reduced heat generation

Publications (1)

Publication Number Publication Date
DE10337019A1 true DE10337019A1 (en) 2005-03-10

Family

ID=34177486

Family Applications (1)

Application Number Title Priority Date Filing Date
DE2003137019 Withdrawn DE10337019A1 (en) 2003-08-12 2003-08-12 Blade of gas turbine, comprising ceramic protection coating with partially polished areas for reduced heat generation

Country Status (1)

Country Link
DE (1) DE10337019A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2725235A1 (en) * 2012-10-24 2014-04-30 Siemens Aktiengesellschaft Differentially rough airfoil and corresponding manufacturing method

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3528861A (en) * 1968-05-23 1970-09-15 United Aircraft Corp Method for coating the superalloys
US4585481A (en) * 1981-08-05 1986-04-29 United Technologies Corporation Overlays coating for superalloys
EP0441095B1 (en) * 1990-02-05 1996-03-06 United Technologies Corporation Method for applying ceramic coatings
DE69504023T2 (en) * 1994-12-24 1998-12-10 Rolls Royce Plc High temperature protective layer for superalloy and method of use
EP1088908A2 (en) * 1999-10-01 2001-04-04 General Electric Company A method for smoothing the surface of a protective coating
EP0937787B1 (en) * 1998-02-19 2002-12-04 United Technologies Corporation Method of applying an overcoat to a thermal barrier coating and coated article
EP1284337A1 (en) * 2001-08-14 2003-02-19 ALSTOM (Switzerland) Ltd Method for machining a coated gas turbine blade and a coated gas turbine blade
US20030041928A1 (en) * 2001-08-31 2003-03-06 Irene Spitsberg Fabrication of an article having a protective coating with a polished, pre-oxidized protective-coating surface

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3528861A (en) * 1968-05-23 1970-09-15 United Aircraft Corp Method for coating the superalloys
US4585481A (en) * 1981-08-05 1986-04-29 United Technologies Corporation Overlays coating for superalloys
EP0441095B1 (en) * 1990-02-05 1996-03-06 United Technologies Corporation Method for applying ceramic coatings
DE69504023T2 (en) * 1994-12-24 1998-12-10 Rolls Royce Plc High temperature protective layer for superalloy and method of use
EP0937787B1 (en) * 1998-02-19 2002-12-04 United Technologies Corporation Method of applying an overcoat to a thermal barrier coating and coated article
EP1088908A2 (en) * 1999-10-01 2001-04-04 General Electric Company A method for smoothing the surface of a protective coating
EP1284337A1 (en) * 2001-08-14 2003-02-19 ALSTOM (Switzerland) Ltd Method for machining a coated gas turbine blade and a coated gas turbine blade
US20030041928A1 (en) * 2001-08-31 2003-03-06 Irene Spitsberg Fabrication of an article having a protective coating with a polished, pre-oxidized protective-coating surface
US6576067B2 (en) * 2001-08-31 2003-06-10 General Electric Co. Fabrication of an article having a protective coating with a polished, pre-oxidized protective-coating surface

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2725235A1 (en) * 2012-10-24 2014-04-30 Siemens Aktiengesellschaft Differentially rough airfoil and corresponding manufacturing method
CN103775134A (en) * 2012-10-24 2014-05-07 西门子公司 Differentially rough blades and manufacturing method thereof

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Legal Events

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OM8 Search report available as to paragraph 43 lit. 1 sentence 1 patent law
8139 Disposal/non-payment of the annual fee