Abstract
The turbine blade in a gas turbine engine operates at a greater temperature than the blade material's melting point. The gas turbine blades cooling is a critical factor for the safe operation of high-performance gas turbines. In the analysis work, the heat transmission of gas turbine blades using two materials and 3 cooling methods is investigated. The cooling of blades has been suggested using a variety of approaches such as internal cooling and film cooling. A turbine blade is designed using CATIAV5-6R. Nickel Chromium, Titanium carbide materials are considered for the study. The CFD software FLUENT is used to analyze the heat transport of a gas turbine blade. Analysis was carried out for internal cooling and film cooling. Titanium carbide has been shown to have better thermal properties than Nickel-Chromium.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
