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    TURBINE BLADE AND GAS TURBINE MEMBER
    1.
    发明专利
    TURBINE BLADE AND GAS TURBINE MEMBER 失效

    公开(公告)号：JP2001214704A

    公开(公告)日：2001-08-10

    申请号：JP2000386529

    申请日：2000-12-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALLEN WILLIAM PATRICK ,  OLSON WALTER E

    IPC: C23C4/00 ,  C23C30/00 ,  F01D5/28

    Abstract: PROBLEM TO BE SOLVED: To improve the durability of a member exposed to high temperature. SOLUTION: A turbine blade 10 for a gas turbine engine is composed of a directionally-solidified metallic base material such as supper alloy, and also has an air foil 12, a root part 14, and a platform 16 positioned between the blade 10 and the part 14. The platform 16 is equipped with a lower surface 18 adjoining the part 14, and aluminide coating including noble metal such as white metal is given to blade portions easily corrosional or crackable in stress corrosion such as the surface 18 or neck part 19 of the platform 16. This coating prevents corrosion or stress-corrosional crack in these regions.

    TURBINE BLADE FOR GAS TURBINE ENGINE
    2.
    发明专利
    TURBINE BLADE FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JP2001234322A

    公开(公告)日：2001-08-31

    申请号：JP2000386526

    申请日：2000-12-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALLEN WILLIAM PATRICK ,  OLSON WALTER E ,  SHAH DILIP M ,  CETEL ALAN DAVID

    IPC: C22C19/00 ,  C23C4/00 ,  C23C4/08 ,  C23C30/00 ,  F01D5/28

    Abstract: PROBLEM TO BE SOLVED: To coat the part of a turbine blade, which is not directly exposed to a high temperature gas flow, with a rust preventive paint for improving the durability of its components. SOLUTION: In this invention, e.g. an article to be exposed to a high temperature of >=1,000 deg.C in the process of its operation is disclosed. In one embodiment, the turbine blade for a gas turbine engine contains a directionally crystallized metallic base, e.g. a superalloy demarcating a profile, a root and a stand arranged between the blade and the root. The stand has a lower side adjacent to the root, and a corrosion resistant lining coating material such as MCrAlY is arranged at the lower side and the cervical part of the stand. The applied coating material prevents the corrosion and stress corrosion cracking of the blade in those regions. Moreover, in the place to be coated with the profile, the coating material for the profile may have a composition different from that of the coating material for the lower face of the stand.

    METHOD OF IMPROVING DURABILITY OF TURBINE BLADE
    3.
    发明专利
    METHOD OF IMPROVING DURABILITY OF TURBINE BLADE 失效

    公开(公告)号：JP2002180231A

    公开(公告)日：2002-06-26

    申请号：JP2000386525

    申请日：2000-12-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALLEN WILLIAM PATRICK ,  OLSON WALTER E ,  SHAH DILIP M ,  CETEL ALAN DAVID

    IPC: F01D5/28 ,  B05B7/16 ,  B05D3/10 ,  B05D5/00 ,  B05D7/14 ,  B05D7/24 ,  C22C19/05 ,  C23C4/02 ,  C23C4/08 ,  C23C4/10

    Abstract: PROBLEM TO BE SOLVED: To improve the durability of a structural element by applying a rust preventing paint on a part of a turbine blade, which is not coated previously and not exposed to a high temperature gas stream. SOLUTION: An article to be exposed to a high temperature, for example, >=1000 deg.C during operating is disclosed. In an embodiment, a method for the gas turbine engine includes a directionally crystallized metallic base, for example a superalloy demarcating a blade profile, a blade root and a pedestal arranged between the blade profile and the blade root. The pedestal has an under side adjacent to the root and a corrosion resistant lining coating material such as MCrAlY, an aluminized compound containing a noble metal or a corrosion resistant ceramic is arranged on a part of the blade, for example, the under side of the pedestal and a neck part, where is not coated with the coating material. The applied coating material prevents the corrosion and the stress corrosion cracking of the blade in the region. A coating material for the blade profile coated with the coating material can have a composition different from the coating material applied on the pedestal under surface.

    ARTICLES HAVING CORROSION RESISTANT COATING.
    4.
    发明专利
    ARTICLES HAVING CORROSION RESISTANT COATING. 未知

    公开(公告)号：MY125231A

    公开(公告)日：2006-07-31

    申请号：MYPI20005894

    申请日：2000-12-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALLEN WILLIAM PATRICK ,  OLSON WALTER E ,  SHAH DILIP M ,  CETEL ALAN DAVID

    IPC: B63H1/26 ,  F01D5/14 ,  F01D5/22

    Abstract: A TURBINE BLADE HAS AN AIR FOIL (12), A ROOT (14) AND A PLATFORM (16) LOCATED BETWEE THE AIRFOIL (12) AND ROOT (14). THE PLATFORM (16) HAS AN UNDERSIDE ADJACENT THE ROOT, AND A CORROSION RESISTANT OVERLAY COATING (21;24) SUCH AS AN MCRAI 1Y OR A NOBLE METAL CONTAINING ALUMINADE OR CORROSION INHIBITING CERAMIC IS LOCATED ON PORTIONS OR THE BLADE NOT PREVIOUSLY COVERED WITH SUCH COATINGS, E.G., THE UNDERSIDE OF THE PLATFORM AND THE NECK (19). THE APPLIED COATING PREVENTS CORROSION AND STRESS CORROSION CRACKING OF BLADE IN THESE REGIONS. WHERE THE AIRFOIL IS ALSO COATED, THE AIRFOIL COATING MAY HAVE A COMPOSITION DIFFERENT FROM THAT OF THE COATING ON THE UNDERPLATFORM SURFACES.[FIG. 1A].

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