Unshrouded turbine blade tip heat transfer and film cooling

Thesis

This thesis presents a joint computational and experimental investigation into the heat transfer to unshrouded turbine blade tips suitable for use in high bypass ratio, large civil aviation turbofan engines. Both the heat transfer to the blade tip and the over-tip leakage flow over the blade tip are characterised, as each has a profound influence on overall engine efficiency.

The study is divided into two sections; in the first, computational simulations of a very large scale, low s...

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Authors: Tang, B; Brian Tang

• Publication date: 2011
• DOI: 10.5287/ora-xmby5paqo
• Type of award: DPhil
• Level of award: Doctoral
• Awarding institution: Oxford University, UK
• Language: English
• Keywords: film cooling; turbomachinery; heat transfer; gas turbine; jet engine; blade tip; aerodynamics; computational fluid dynamics; CFD; fluid flow; turbine
• Subjects: Turbomachinery hypersonics and aerodynamics; Aerodynamics and heat transfer; Mechanical engineering; Aero engines; Engineering & allied sciences