Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Siemens Energy, Inc.

Dimitrios Zois

Ramesh Subramanian

Cora Schillig

Neil Hitchman

Ching-Pang Lee

Gary Brian Merrill

Kok-Mun Tham

Gm Salam Azad

Arturo Flores Renteria

Zhihong Gao

David G Sansom

Jonathan E Shipper

Alexandr Sadovoy

Jonathan E Shipper, Jr

Barrry L Allmon

Peter Stuart Hollingsworth

A seal system for gas turbine that includes a stator and a blade with a blade tip facing the stator. The blade has a protective ceramic coating having an inner ceramic layer being made of a partially stabilized zirconia and having at least a partially segmented microstructure in form of vertical cracks. The ceramic coating further includes an outer ceramic layer made of fully stabilized zirconia and having a segmented microstructure. Advantageously, the entire airfoil surface is provided with the protective ceramic coating. With the fully stabilized zirconia coating on the tip of a blade which faces a casing with a ceramic coating, a result is a better sealing system. The stator includes an abradable coating having at least an outer ceramic coating being made of fully stabilized or ytterbium stabilized zirconia.

Fully stabilized zirconia in a seal system

An improved ceramic material for heat insulation with selection of specific stabilizers and adapted proportions, includes zirconium oxide with 0.2 wt. % to 8.0 wt. % of the base stabilizers: yttrium oxide (YO), hafnium oxide (HfO), cerium oxide (CeO), calcium oxide (CaO), and/or magnesium oxide (MgO), wherein at least yttrium oxide (YO) is used, and optionally at least one of the additional stabilizers: 0.2 wt. % to 20 wt. % of erbium oxide (ErO) and/or ytterbium oxide (YbO).

Ceramic material, powder, and layer system comprising the ceramic material

A method to increase the thermal stress capability of a porous TBC and layer system. Due to a post treatment step to a pose TBC coating cracks are produced inside the post TBC advantages manner to increase the thermal stress capability of the ceramic coating by only heating the surface of the ceramic coating.

Method to increase the thermal stress capability of a porous ceramic coating and a layer system

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.

Turbine component thermal barrier coating with crack isolating engineered groove features

Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of ridges in planform patterns, establishing upper and lower wear zones. The lower wear zone reduces, redirects and/or blocks blade tip downstream airflow leakage, while the upper wear zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. An elongated first ridge in the lower wear zone terminates in a continuous surface plateau. A plurality of second ridges or nibs, separated by grooves, project from the plateau, forming the upper wear zone. Each of the second ridges has a planform cross section smaller than the plateau planform cross section and a height smaller than the first ridge height. Some embodiments of the second ridges have spacing, planform cross sections, heights and separating groove dimensions selected for shearing when contacted by turbine blade tips.

Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface

Growing community of inventors

Berlin, Germany

Dimitrios Zois