Thermal control of gas turbine casings for improved tip clearance

Thesis

A thermal tip clearance control system provides a robust and flexible means of manipulating the closure between the casing and the rotating blade tips in a jet engine, reducing undesirable tip leakage flows. This may be achieved using an impingement cooling scheme on the external casing of the engine in conjunction with careful thermal management of internal over-tip seal segment cavity. For a reduction in thrust specific fuel consumption, the mass flow rate of air used for cooling must ...

Expand abstract

Authors: Choi, M

• DOI: 10.5287/ora-z5b4wxg5x
• Type of award: DPhil
• Level of award: Doctoral
• Awarding institution: University of Oxford
• Language: English
• Keywords: Seal segment; Blade tip clearance; Gas turbine casing; Thermomechanical; Cooling manifold; Aerothermal; Thermal clearance control; Impingement cooling
• Subjects: Turbomachinery; Aerodynamics and heat transfer