The increase in gas turbine performance allows for very high total inlet temperatures even in heavy duty applications. Therefore, an accurate rotor blade cooling design is necessary to obtain very high reliability and efficiency. This paper presents a simple and fast procedure to study global cooling systems and to evaluate a blade temperature distribution in a cooled rotor cascade. The blade cooling design is developed by a modular approach: it allows one to select any combination of several cooling techniques.
A Rotor Blade Cooling Design Method For Heavy Duty Gas Turbine / B. FACCHINI; CARCASCI C.; FERRARA G.. - STAMPA. - (1995), pp. 1-8. (Intervento presentato al convegno ASME paper 95-CTP-90 VIII° ASME Cogenturbo tenutosi a Vienna, Austria nel 23-25 August 1995).
A Rotor Blade Cooling Design Method For Heavy Duty Gas Turbine
FACCHINI, BRUNO;CARCASCI, CARLO;FERRARA, GIOVANNI
1995
Abstract
The increase in gas turbine performance allows for very high total inlet temperatures even in heavy duty applications. Therefore, an accurate rotor blade cooling design is necessary to obtain very high reliability and efficiency. This paper presents a simple and fast procedure to study global cooling systems and to evaluate a blade temperature distribution in a cooled rotor cascade. The blade cooling design is developed by a modular approach: it allows one to select any combination of several cooling techniques.
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