Damage of Coated Turbine Blades after Overheating Events

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F11%3APU96855" target="_blank" >RIV/00216305:26210/11:PU96855 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Damage of Coated Turbine Blades after Overheating Events

Popis výsledku v původním jazyce

Turbine blades of aircraft engines are the most loaded parts owing to the high working temperature, induced mechanical stresses as well as an abrasive and corrosive environment. The metallic coatings on blades serve as physical barriers protecting the underlying substrate from these severe degradation effects. One of the most serious degradation modes of coatings is their creep degradation during overheating events. If the critical temperature of gases becomes significantly higher than the nominal one, the surface layer of the blades suffers from initiation of microcracks and cavities in a very short time. Growing of these defects then leads to spalling and progressive destruction of the coating during the further service. This article presents examples of coatings on rotor blades of high-pressure turbines in aircraft engines that were degraded after overheating events during the service. These diffusion aluminide coatings are based on the intermetallic compound beta-NiAl that forms under the influenc

Název v anglickém jazyce

Damage of Coated Turbine Blades after Overheating Events

Popis výsledku anglicky

Turbine blades of aircraft engines are the most loaded parts owing to the high working temperature, induced mechanical stresses as well as an abrasive and corrosive environment. The metallic coatings on blades serve as physical barriers protecting the underlying substrate from these severe degradation effects. One of the most serious degradation modes of coatings is their creep degradation during overheating events. If the critical temperature of gases becomes significantly higher than the nominal one, the surface layer of the blades suffers from initiation of microcracks and cavities in a very short time. Growing of these defects then leads to spalling and progressive destruction of the coating during the further service. This article presents examples of coatings on rotor blades of high-pressure turbines in aircraft engines that were degraded after overheating events during the service. These diffusion aluminide coatings are based on the intermetallic compound beta-NiAl that forms under the influenc

Druh

O - Ostatní výsledky

CEP obor

JL - Únava materiálu a lomová mechanika

OECD FORD obor

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Projekt

<a href="/cs/project/FR-TI1%2F099" target="_blank" >FR-TI1/099: *Výzkum a vývoj vedoucí k inovaci malých turbínových motorů.</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2011

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů