Numerical study and heat transfer analysis of nickel-chromium and titanium carbide gas turbine blades cooling

被引：3

作者：

Ahmed, Syed Irfan ^{[1
]}

Balguri, Praveen Kumar ^{[1
]}

Govardhan, D. ^{[1
]}

Habeeb, Syed ^{[1
]}

机构：

[1] Inst Aeronaut Engn, Dept Aeronaut Engn, Hyderabad 500 043, India

来源：

MATERIALS TODAY-PROCEEDINGS | 2022年 / 62卷

关键词：

Gas turbine blade; Heat transfer; Thermal analysis; Titanium carbide; Nickel-chromium;

D O I：

10.1016/j.matpr.2021.12.033

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

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 highperformance 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 NickelChromium. Copyright (c) 2022 Elsevier Ltd. All rights reserved. Selection and peer-review under responsibility of the scientific committee of the International Conference on Materials, Processing & Characterization

引用

页码：2709 / 2713

页数：5

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