Thermostressed State in Turbine Rotor Blades with Thermal Barrier Coating at Transient Conditions of Air Breathing Jet Engine Operation

V. A. Trushin

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Thermostressed State in Turbine Rotor Blades with Thermal Barrier Coating at Transient Conditions of Air Breathing Jet Engine Operation

机译：空气呼吸喷气发动机运行瞬态条件下具有热障涂层的涡轮转子叶片的热应力状态

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摘要

The finite-difference method acceptable for on-board computers is applied to analyze the thermo-stressed state for the thermal-barrier coating of a perforated turbine blade and its wall at transient and stationary conditions of air-breathing jet engine operation during a flight.

机译：机载计算机可接受的有限差分方法用于分析在飞行过程中呼吸喷气发动机运行的瞬态和静止条件下穿孔涡轮机叶片及其壁的热障涂层的热应力状态。

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来源
《Russian Aeronautics》 |2013年第4期|共7页
作者
V. A. Trushin;
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原文格式 PDF
正文语种 eng
中图分类航空;
关键词
Turbine blade; Perforation; Thermal barrier coating; Components; Thermophysical properties; Temperature; Stress;

机译：涡轮叶片;穿孔;热障涂层;部件;热物理性质;温度;应力;

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专利

1. Thermostressed State in Turbine Rotor Blades with Thermal Barrier Coating at Transient Conditions of Air Breathing Jet Engine Operation [J] . V. A. Trushin Russian Aeronautics . 2013,第4期

机译：空气呼吸喷气发动机运行瞬态条件下具有热障涂层的涡轮转子叶片的热应力状态
2. Damage evolution in EB-PVD thermal barrier coatings for turbine blades in aircraft engines under close to reality testing conditions [J] . M.Bartsch, G.Marci, K.Mull International journal of materials & product technology . 2001,第1a2a3期

机译：在接近实际测试条件下，用于飞机发动机涡轮叶片的EB-PVD热障涂层的损伤演变
3. THERMAL BARRIER COATING OF A TURBINE BLADE IN THE GTE TRANSIENT OPERATING CONDITIONS [J] . V. A. Trushin, O. V. Trushin Russian Aeronautics . 2006,第4期

机译：GTE瞬态运行条件下涡轮叶片的热障涂层
4. Synchrotron XRD Measurements of Thermal Barrier Coatings Subjected to Loads Representing Operational Conditions of Rotating Gas Turbine Blades [C] . Kevin Knipe, Albert Manero, Sanna F. Siddiqui, AIAA SciTech forum;Aerospace sciences meeting . 2014

机译：承受代表旋转燃气轮机叶片运行条件的载荷的热障涂层的同步XRD测量
5. Chemical vapor deposition of yttria-stabilized zirconia as a thermal barrier coating for gas turbine engines. [D] . Varanasi, Venu Gopal. 2004

机译：氧化钇稳定的氧化锆的化学气相沉积，作为燃气轮机的隔热涂层。
6. 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

机译：封面文章：理论上的涡轮发动机隔热涂层的原子尺度见解和设计原理
7. A new spallation mechanism of thermal barrier coatings on aero-engine turbine blades [O] . Yuan, Bo, Harvey, Christopher M., Thomson, Rachel C., 2018

机译：航空发动机涡轮叶片上隔热涂层的新散裂机理
8. DURABILITY OF ZIRCONIA THERMAL BARRIER CERAMIC COATINGS ON AIR-COOLED TURBINE BLADES IN CYCLIC JET ENGINE OPERATION [R] . Curt H. Liebert, Richard E. Jacobs, Stephan Stecura 1976

机译：循环射流发动机运行中空气冷却涡轮叶片上氧化锆热障涂层的耐久性

Thermostressed State in Turbine Rotor Blades with Thermal Barrier Coating at Transient Conditions of Air Breathing Jet Engine Operation

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