Novel cooling design for blade or vane trailing edges

Thesis

The trailing edge of the high pressure turbine blade and vane presents significant challenges to the turbine cooling engineer. This section endures very high temperature and mechanical stresses but aerodynamic efficiency requirements dictate that it must be tapered to the end with minimal thickness, making it difficult to cool internally. Pressure side film cooling using a slot has become a common and effective method to cool the trailing edge by creating a sheet of coolant which protects ...

Expand abstract

Authors: Wong, T

• Type of award: DPhil
• Level of award: Doctoral
• Awarding institution: University of Oxford
• Language: English
• Keywords: Turbomachinery; Vane; Pressure sensitive paint; Blade; Jet engines; Trailing edge; Turbine; Cooling; Film effectiveness
• Subjects: Thermofluids; Turbomachinery; Heat transfer; Turbine cooling; Jet engines