公开(公告)号：US20160369637A1

公开(公告)日：2016-12-22

申请号：US15121513

申请日：2015-02-18

Applicant: Siemens Aktiengesellschaft

Inventor： Ramesh SUBRAMANIAN ,  Stefan LAMENSCHERF ,  Cora SCHILLIG ,  Neil HITCHMAN ,  Dimitrios ZOIS

IPC: F01D5/28 ,  C23C16/22 ,  C23C4/134 ,  F01D9/04 ,  F01D9/02

CPC classification number: F01D5/187 ,  C23C4/02 ,  C23C4/134 ,  C23C16/22 ,  F01D5/286 ,  F01D5/288 ,  F01D9/023 ,  F01D9/041 ,  F01D11/122 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2250/13 ,  F05D2250/28 ,  F05D2260/202 ,  F05D2300/10 ,  F05D2300/5023 ,  F05D2300/611

Abstract: Thermal barrier coatings (TBCs) for turbine engine components are applied over engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC. The ESFs help anchor the TBC layer and/or localize cracks that are bounded by one or more of the ESFs. During engine operation the ESFs arrest 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. In some embodiments, the ESFs are combined with engineered groove features that are formed in the TBC.

Abstract translation: 用于涡轮发动机部件的热障涂层（TBC）应用于在组件衬底中形成的工程表面特征（ESF）上，或者施加在衬底和TBC之间的中间层内。 ESFs帮助锚定TBC层和/或定位由一个或多个ESF界定的裂缝。 在发动机运行期间，ESF阻止了TBC内的热应力或异物损伤（FOD）引起的裂纹扩展，否则可能会导致TBC的过度剥落和随后对基底下的涡轮部件的热暴露损坏。 在一些实施例中，ESF与在TBC中形成的工程化凹槽特征组合。

公开(公告)号：US20170175560A1

公开(公告)日：2017-06-22

申请号：US15128578

申请日：2015-02-18

Applicant: SIEMENS AKTIENGESELLSCHAFT

Inventor： Gary B. MERRILL ,  Marco Claudio Pio BRUNELLI ,  Jonathan E. SHIPPER Jr. ,  David G. SANSOM ,  Cora SCHILLIG ,  Dimitrios ZOIS ,  Neil HITCHMAN

IPC: F01D11/12 ,  F01D5/28

CPC classification number: F01D11/122 ,  C23C4/04 ,  C23C4/12 ,  F01D5/18 ,  F01D5/187 ,  F01D5/288 ,  F01D9/02 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2250/00 ,  F05D2250/141 ,  F05D2250/18 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/185 ,  F05D2250/23 ,  F05D2250/28 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/231 ,  F05D2260/941 ,  F05D2300/10 ,  F05D2300/21 ,  F05D2300/5023 ,  F05D2300/516 ,  F05D2300/611

Abstract: A turbine abradable component includes a support surface and a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface for orientation proximal a rotating turbine blade tip circumferential swept path. An elongated pixelated major planform pattern (PMPP) of a plurality of discontinuous micro surface features (MSF) project from the substrate surface. The PMPP repeats radially along the swept path in the blade tip rotational direction, for selectively directing airflow between the blade tip and the substrate surface. Each MSF is defined by a pair of first opposed lateral walls defining a width, length and height that occupy a volume envelope of 1-12 cubic millimeters. The PMPP arrays of MSFs provide airflow control of hot gasses in the gap between the abradable surface and the blade tip with smaller potential rubbing surface area than solid projecting ribs with similar planform profiles.