公开(公告)号：WO2015130527A3

公开(公告)日：2015-12-03

申请号：PCT/US2015016324

申请日：2015-02-18

Applicant: SIEMENS AG ,  SIEMENS ENERGY INC

Inventor： HITCHMAN NEIL ,  SUBRAMANIAN RAMESH ,  SCHILLIG CORA

IPC: F01D11/12 ,  F01D11/08

CPC classification number: F01D11/122 ,  B22C7/02 ,  B22C9/24 ,  B22D25/02 ,  B22D29/001 ,  C23C4/02 ,  C23C4/073 ,  C23C4/18 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/023 ,  F01D11/08 ,  F01D11/127 ,  F01D25/12 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/211 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2250/12 ,  F05D2250/15 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2250/23 ,  F05D2250/282 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/60 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2300/175

Abstract: A thermal barrier coating (TBC) with depth-varying material properties is formed on a turbine component. Exemplary depth-varying material properties include physical ductility, strength and thermal resistivity that vary from the TBC layer inner to outer surface. Exemplary ways to modify physical properties include application of plural separate overlying layers of different material composition or by varying the applied material composition during the application of the TBC layer. Various embodiment described herein also apply a calcium-magnesium-aluminum-silicon (CMAS)-retardant material over the TBC layer to retard reaction with or adhesion of CMAS containing combustion particulates to the TBC layer. In other embodiments the CMAS retardant material is also applied within engineered groove features (EGFs) that are formed in the TBC surface.

Abstract translation: 在涡轮机部件上形成具有深度变化材料特性的热障涂层（TBC）。 示例性的深度变化材料性质包括从TBC层内表面到外表面不同的物理延展性，强度和热阻率。 改变物理性质的示例性方法包括施加不同材料组成的多个分开的叠置层，或通过在施加TBC层期间改变所施加的材料组成。 本文所述的各种实施方式还在TBC层上应用钙 - 镁 - 铝 - 硅（CMAS） - 延迟材料以阻止含有燃烧颗粒的CMAS与TBC层的反应或粘附。 在其他实施方案中，CMAS阻滞剂材料也应用于在TBC表面中形成的工程化凹槽特征（EGF）内。

公开(公告)号：WO2015130526A3

公开(公告)日：2016-06-16

申请号：PCT/US2015016318

申请日：2015-02-18

Applicant: SIEMENS AG

Inventor： SUBRAMANIAN RAMESH ,  HITCHMAN NEIL ,  ZOIS DIMITRIOS ,  SHIPPER JR JONATHAN E ,  HITCHMAN CORA

IPC: F01D11/08 ,  F01D5/18 ,  F01D11/12

CPC classification number: F01D11/122 ,  B22C7/02 ,  B22C9/24 ,  B22D25/02 ,  B22D29/001 ,  C23C4/02 ,  C23C4/073 ,  C23C4/18 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/023 ,  F01D11/08 ,  F01D11/127 ,  F01D25/12 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/211 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2250/12 ,  F05D2250/15 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2250/23 ,  F05D2250/282 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/60 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/22141 ,  F05D2300/175

Abstract: Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensional or polygonal planform pattern on the TBC surface and into the TBC layer. The EGFs localize thermal stress- or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. Propagation of a crack is arrested when it reaches an EGF, so that it does not cross over the groove to otherwise undamaged zones of the TBC layer. In some embodiments, the EGFs are combined with engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC.

Abstract translation: 在涡轮发动机部件的热障涂层（TBC）内形成工程槽特征（EGF）。 EGF有利地与TBC内的可能的应力区域对准，或者以TBC表面和TBC层中的方便的二维或多边形平面图案随机排列。 EGF将局部热应激或异物损伤（FOD）引起TBC内的裂纹扩展，否则可能会导致过度的TBC剥落和随后对基底下的涡轮部件的热暴露损伤。 裂缝的传播在到达EGF时被阻止，使得它不会越过沟槽到TBC层的未损坏的区域。 在一些实施方案中，EGF与在组分衬底中形成的工程化表面特征（ESF）或施加在衬底和TBC之间的中间层内组合。