Nowadays total inlet temperature of gas turbine is far above the permissible metal temperature, advanced cooling technique must be applied to protect several components located in the high pressure stages, such as turbine buckets, reducing risk of creep failures. Film cooling has been widely used to control temperature of high temperature and high pressure blades. In a film cooled blade the air taken from last compressor stages is ejected through discrete holes drilled on blade surface to provide a cold layer between hot mainstream and turbine components. A comprehensive understanding of phenomena concerning the complex interaction of hot gasses with coolant flows in a vane passage plays a major role in the definition of a well performing film cooling scheme. The present work aims at deepening the knowledge on the adiabatic effectiveness distributions on a real turbine bucket by means of coolant concentration technique based on Pressure Sensitive Paint (PSP). The experimental survey was performed on a static test article replicating an annular sector made up of two turbine buckets and three passages, designed to achieve Reynolds and Mach mainstream number similarity. A real turbine bucket, with complete internal cooling scheme fed through a plenum chamber has been tested with different coolant and mainstream conditions. Film cooling was generated by a showerhead on leading edge, shaped holes on suction side and cylindrical holes on pressure side. Results, reported in terms of detailed 2D maps of film cooling effectiveness, point out the effect of coolant/mainstream mass ratio; furthermore results in terms of 1D adiabatic effectiveness trends have been reported for suction side shaped holes.

Film-cooling adiabatic effectiveness measurements on a real high pressure turbine blade / Bruno Facchini; Alessio Picchi; Lorenzo Tarchi; Alessandro Ciani; Michele D’Ercole; Luca Innocenti. - ELETTRONICO. - (In corso di stampa), pp. 0-0. (Intervento presentato al convegno 10th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics).

Film-cooling adiabatic effectiveness measurements on a real high pressure turbine blade

FACCHINI, BRUNO;PICCHI, ALESSIO;
In corso di stampa

Abstract

Nowadays total inlet temperature of gas turbine is far above the permissible metal temperature, advanced cooling technique must be applied to protect several components located in the high pressure stages, such as turbine buckets, reducing risk of creep failures. Film cooling has been widely used to control temperature of high temperature and high pressure blades. In a film cooled blade the air taken from last compressor stages is ejected through discrete holes drilled on blade surface to provide a cold layer between hot mainstream and turbine components. A comprehensive understanding of phenomena concerning the complex interaction of hot gasses with coolant flows in a vane passage plays a major role in the definition of a well performing film cooling scheme. The present work aims at deepening the knowledge on the adiabatic effectiveness distributions on a real turbine bucket by means of coolant concentration technique based on Pressure Sensitive Paint (PSP). The experimental survey was performed on a static test article replicating an annular sector made up of two turbine buckets and three passages, designed to achieve Reynolds and Mach mainstream number similarity. A real turbine bucket, with complete internal cooling scheme fed through a plenum chamber has been tested with different coolant and mainstream conditions. Film cooling was generated by a showerhead on leading edge, shaped holes on suction side and cylindrical holes on pressure side. Results, reported in terms of detailed 2D maps of film cooling effectiveness, point out the effect of coolant/mainstream mass ratio; furthermore results in terms of 1D adiabatic effectiveness trends have been reported for suction side shaped holes.
In corso di stampa
10th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics
10th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics
Bruno Facchini; Alessio Picchi; Lorenzo Tarchi; Alessandro Ciani; Michele D’Ercole; Luca Innocenti
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Utilizza questo identificatore per citare o creare un link a questa risorsa: https://hdl.handle.net/2158/795054
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