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    12.
    发明专利
    未知

    公开(公告)号：FR2895741B1

    公开(公告)日：2009-02-27

    申请号：FR0609445

    申请日：2006-10-27

    Applicant: SIEMENS AG

    Inventor： SCHUMANN ECKART ,  SUBRAMANIAN RAMESH

    IPC: C04B35/48 ,  B32B18/00 ,  C23C30/00

    Abstract: The thermal barrier coating system applied to a substrate for gas turbine blades/vanes/heat shields, comprises a metallic bonding layer having NiCoCrAlX alloy, an inner ceramic layer (10) on the metallic bonding layer, and an outer ceramic layer (13) on the inner ceramic layer. The inner layer has a thickness of 40-50% of the total thickness of the inner and the outer layer. The inner layer has a thickness of 50 mu m. The total thickness amounts of the inner and the outer layer are 600 mu m. An independent claim is included for a metallic component.

    15.
    发明专利
    未知

    公开(公告)号：DE50204605D1

    公开(公告)日：2006-03-02

    申请号：DE50204605

    申请日：2002-03-28

    Applicant: SIEMENS AG

    Inventor： JANSING THOMAS ,  FLECK ROBERT ,  SCHUMANN ECKART

    IPC: C01F7/16 ,  C23C4/02 ,  C23C4/11 ,  C23C28/00 ,  C23C30/00 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00 ,  F02C7/30

    Abstract: The blade body (15) is a Ni- or Co-based superalloy with two different ceramic insulating layers (31, 33) applied to it. The second layer (33) has the following composition, expressed in wt%: (i) 10-95 magnesium aluminate; (ii) 5-90 magnesium oxide; (iii) 0-20 aluminum oxide. The residue comprises normal impurities. Grains (23) of magnesium oxide are embedded in the matrix of spinel-structured magnesium aluminate, having a mean diameter of 0.1-10 mu m. The first layer (31) comprises yttrium oxide (Y2O3) -stabilized zirconium dioxide. The porosity of the layers (31, 32) exceeds 3 vol%.

    Protective coating for turbine components
    18.
    发明专利
    Protective coating for turbine components 未知

    公开(公告)号：GB2439312A

    公开(公告)日：2007-12-27

    申请号：GB0612214

    申请日：2006-06-20

    Applicant: SIEMENS AG

    Inventor： KAISER AXEL ,  SCHUMANN ECKART ,  SUBRAMANIAN RAMESH

    IPC: C23C28/00 ,  F01D5/28

    Abstract: A coating system 1 comprising a specially adapted layer sequence of layers including a metallic bonding layer 7, an inner ceramic layer 10 of stabilised zirconia and an outer ceramic layer 13 comprising at least 80% of a pyrochlore. The pyrochlore may be selected from Gd2Zr2O7, or Gd2Hf2O7, the inner ceramic layer may be yytrium stabilised zirconia, and the metallic bonding layer may be a cobalt or nickel based alloy. The coating system is used to protect superalloy turbine components etc.

    Thermal barrier coating system incorporating a pyrochlore.
    20.
    发明专利
    Thermal barrier coating system incorporating a pyrochlore. 未知

    公开(公告)号：GB2432591A

    公开(公告)日：2007-05-30

    申请号：GB0623305

    申请日：2006-11-22

    Applicant: SIEMENS AG

    Inventor： KAISER AXEL ,  SCHUMANN ECKART ,  SUBRAMANIAN RAMESH

    IPC: C23C28/00 ,  F01D5/28

    Abstract: A thermal barrier coating system 1 comprising an outer ceramic layer 13 of pyrochlore structure Gdv(ZrxHFy)Oz., preferably Gd2(ZrxHFy)O7, deposited on a substrate 4. This outer ceramic layer includes a solid solution of gadolinium zirconate and gadolinium hafnate. The ratio of hafnium to zirconium present can vary. Preferably an inner ceramic layer 13 comprising yttrium stabilized zirconium and a metallic bonding layer 7 of a NiCoCrAlX alloy are also present beneath the outer ceramic layer. The coating system is useful for turbine blades or vanes.

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