Fatigue Failure on Turbine Blade(large subsonic aircraft)

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SUMMARY

The discussion focuses on selecting materials for turbine blades in large subsonic aircraft, particularly nickel-based alloys. CMSX-4 is identified as a preferred material, along with the manufacturing techniques of directional solidification and single crystal growth. The conversation highlights the importance of ceramic coatings in extending turbine blade lifespan. Additionally, participants seek historical data on turbine blade materials from the 1940s to present and inquire about the relationship between turbine blade performance and fatigue failure mechanisms.

PREREQUISITES
  • Understanding of nickel-based alloys used in gas turbines
  • Knowledge of turbine blade manufacturing techniques, specifically directional solidification and single crystal growth
  • Familiarity with ceramic coatings and their applications in aerospace
  • Awareness of fatigue failure mechanisms such as corrosion-fatigue, creep-fatigue, and thermal-fatigue
NEXT STEPS
  • Research the properties and applications of CMSX-4 in turbine blades
  • Explore the historical development of turbine blade materials from the 1940s to present
  • Investigate the effects of ceramic coatings on turbine blade performance and longevity
  • Study the relationship between turbine blade design and various fatigue failure mechanisms
USEFUL FOR

Aerospace engineers, materials scientists, and professionals involved in the design and manufacturing of turbine blades for aircraft engines will benefit from this discussion.

billcc
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I am doing a project on the subject above, and i am selecting one type of material that is currently popular used in gas turbine, but i found it difficult to select the material as there are too many nickel-based alloy that can be use for this application. Can anyone direct me with a suggestion on what type of materials should i choose and any specific link that can provide the properties of the material?

Besides that, i am looking for development of turbine blade material used since 1940s until now, but i can't seems to find any relevant info on it. Can anyone share some info regarding this?

by the way, from my readings, i found that nowadays, mostly turbine blade are produce to be single crystal plus enhancement of properties with coatings. Is this true for the application of aircraft engine turbine blade available nowadays?
 
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Astronuc said:
See this thread - https://www.physicsforums.com/showthread.php?t=242166

Directional solidification and single crystal are preferred methods for turbine blade manufacture.

Ceramic coatings extend the lifetime.

Dear Astronuc,
regarding this thread, this link below seems to be unavailable:
http://www.eprictcenter.com/infocenter/ct_o_and_m/pdf/creep7_paper02_msw.pdf

this link seems to have statistic that i wanted, are there any similar link that i can make use?
by the way, does CMSX-4 belong to the preferred materials used for turbine blade nowadays?

are there any link that relate the performance of turbine blade with the fatigue failure mechanism? such as, corrosion-fatigue, creep-fatigue, thermal-fatigue, etc.

thanks for showing me such a useful thread.
 
Last edited by a moderator:
It could be the site is down, or they've changed the url, or they no longer have the paper available.

The paper may no longer be available. One could contact the authors:

Materials Technology for Advanced Land Based Gas Turbines
R. Viswanathan, Ph.D., EPRI, Palo Alto, CA 94304, USA
S. T. Scheirer, Ph.D., Power Tech Associates, Media, PA 19063, USA

Meanwhile try this -
http://www.netl.doe.gov/technologies/coalpower/turbines/refshelf/handbook/4.4.1.pdf

http://www.osti.gov/bridge/servlets/purl/72949-XICguK/webviewable/72949.pdf

http://www.gepower.com/prod_serv/products/tech_docs/en/downloads/ger3569g.pdf

CMSX-4 is one of the preferred materials.
 
Last edited by a moderator:

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