首页> 外国专利> TURBINE COMPONENT THERMAL BARRIER COATING WITH VERTICALLY ALIGNED, ENGINEERED SURFACE AND MULTIFURCATED GROOVE FEATURES

TURBINE COMPONENT THERMAL BARRIER COATING WITH VERTICALLY ALIGNED, ENGINEERED SURFACE AND MULTIFURCATED GROOVE FEATURES

机译：涡轮组件热障涂层，具有垂直对齐的，工程化的表面和多通道沟槽特征

页面导航

摘要
著录项
相似文献

摘要

Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove features (EGFs) (642, 652). A planform pattern of EGFs (642, 652) is cut into the outer surface of the component's thermal barrier coating (TBC). The EGF pattern includes a planform pattern of overlying vertices (644) respectively in vertical alignment with an underlying corresponding ESF (632, 634). At least three respective groove segments (642, 652, 642) within the EGF pattern (640) converge at each respective vertex (644) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σ_A) is furcated (σ_B, σ_C) at each successive vertex juncture.

机译：涡轮发动机（ 80 ）组件，例如叶片（ 92 ），叶片（ 104、106 ），环段 110 耐磨表面 120 或过渡（ 85 ）具有垂直对齐的工程表面特征（ESF）（ 632、634 ）和分叉工程凹槽特征（EGF）（ 642、652 ）。 EGF（ 642，652 ）的平面图案被切入该部件的隔热涂层（TBC）的外表面。 EGF模式包括分别与基础对应的ESF（ 632、634 ）垂直对齐的重叠顶点（ 644 ）的平面样式。 EGF模式（ 640 ）中的至少三个相应的槽段（ 642、652、642 ）会聚在其中的每个相应顶点（ 644 ）一个多分支的模式，当应力（σ_{A ）被分叉（σ_{B ，σ_{C ）在每个连续的顶点接合处。}}} 展开▼

著录项

公开/公告号US2018066527A1

专利类型

公开/公告日2018-03-08

原文格式PDF

申请/专利权人 SIEMENS AKTIENGESELLSCHAFT;
展开▼

申请/专利号US201515547709

发明设计人 KAI KADAU;JOSE ANTONIO PASCUAL-GUTIERREZ;ATIN SHARMA;
展开▼

申请日2015-12-08

分类号F01D5/28;F01D11/12;F01D5/18;C23C28;C23C4/18;C23C4/073;C23C4/02;

国家 US

入库时间 2022-08-21 12:59:29

相似文献

专利

外文文献

中文文献

1. 具有裂纹隔离工程化表面特征件的涡轮部件热障涂层 [P] . 中国专利： CN106030043B . 2018.12.07

2. 具有裂纹隔离工程化表面特征件的涡轮部件热障涂层 [P] . 中国专利： CN106030043A . 2016-10-12

3. TURBINE COMPONENT THERMAL BARRIER COATING WITH VERTICALLY ALIGNED, ENGINEERED SURFACE AND MULTIFURCATED GROOVE FEATURES [P] . 欧洲知识产权局专利： EP3259453A1 . 2017-12-27

机译：涡轮组件热障涂层，具有垂直对齐的，工程化的表面和多通道沟槽特征

4. TURBINE COMPONENT THERMAL BARRIER COATING WITH VERTICALLY ALIGNED, ENGINEERED SURFACE AND MULTIFURCATED GROOVE FEATURES [P] . 世界知识产权组织专利： WO2016133580A1 . 2016-08-25

机译：涡轮组件热障涂层，具有垂直对齐的，工程化的表面和多通道沟槽特征

5. TURBINE COMPONENT THERMAL BARRIER COATING WITH CRACK ISOLATING, CASCADING, MULTIFURCATED ENGINEERED GROOVE FEATURES [P] . 美国专利： US2018010469A1 . 2018-01-11

机译：涡轮组件热障涂层，具有裂纹隔离，级联，多用途工程沟槽特征

1. A new spallation mechanism of thermal barrier coatings on aero-engine turbine blades [J] . Bo Yuan, Christopher M. Harvey, Rachel C. Thomson, 力学快报(英文版) . 2018,第001期

2. Quantitative assessment of the surface crack density in thermal barrier coatings [J] . Li Yang, Zhi-Chun Zhong, Yi-Chun Zhou, 力学学报：英文版 . 2014,第002期

3. Investigation on surface figuration and microstructure of laser glazed nanostructure zirconia thermal barrier coatings [J] . 黄炳华, 王红英, 郝云飞, 中国焊接：英文版 . 2009,第001期

4. Effects of carbon content in iron catalyst coatings on the growth of vertically aligned carbon nanotubes on smooth silicon surfaces by thermal chemical vapor deposition [J] . C. Liu, Y. C. Chen, Y. Tzeng Diamond and Related Materials . 2004,第4a8期

5. Practical Aspects of Suspension Plasma Spray for Thermal Barrier Coatings on Potential Gas Turbine Components [J] . X. Ma, P. Ruggiero Journal of Thermal Spray Technology . 2018,第4期

6. PRACTICAL ASPECTS OF SUSPENSION PLASMA SPRAY FOR THERMAL BARRIER COATINGS ON POTENTIAL GAS TURBINE COMPONENTS [J] . Ma X., Ruggiero P. Advanced Materials & Processes . 2018,第5期

7. Development of NiCrAlY alloys for corrosion resistant coatings and thermal barrier coatings of gas turbine components [C] . Hubertus Nickel, Doris Clemens, Willem J.Quadakkers, ASME/JSME joint pressure vessels and piping conference . 1998

8. Degradation of thermal barrier coatings on an Integrated Gasification Combined Cycle (IGCC) simulated film-cooled turbine vane pressure surface due to particulate fly ash deposition [D] . Luo, Kevin 2014

9. Inaugural ArticleFrom the Cover: Atomic-scale insight and design principles for turbine engine thermal barrier coatings from theory [O] . Kristen A. Marino, Berit Hinnemann, Emily A. Carter 2011

10. Failure mechanisms of thermal barrier coatings for high temperature gas turbine components under cyclic thermal loading [O] . Postolenko Vitalii 2008

11. Advance Turbine System Conceptual Design and Product Development. Topical Report for Non-Destructive Techniques for the Evaluation of Overlay and Thermal Barrier Coatings on Gas Turbine Components. (Task 8.2.4.2). [R] . Cybulsky, M. 1998

1. Effects of Syngas Particulate Fly Ash Deposition on the Mechanical Properties of Thermal Barrier Coatings on Simulated Film-Cooled Turbine Vane Components [J] . Kevin Luo ,Andrew C. Nix ,Bruce S. Kang . 清洁煤炭能国际期刊（英文） . 2014,第4期

2. Microstructural Degradation of Thermal Barrier Coatings on an Integrated Gasification Combined Cycle (IGCC) Simulated Film-Cooled Turbine Vane Pressure Surface Due to Particulate Fly Ash Deposition [J] . Kevin Luo ,Andrew C. Nix ,Edward M. Sabolsky . 清洁煤炭能国际期刊（英文） . 2015,第1期

3. 具有垂直裂纹的热障涂层有限元应力计算 [C] . . 2008年(第十届)中国科协年会 . 2008

4. 基于流-固耦合的三维涡轮叶片热障涂层危险区域预测的数值模拟 [A] . 王军武 . 2016