Authors:
V. Zubanov
;
G. M. Popov
;
S. Melnikov
;
A. I. Sherban
and
Liu Xin
Affiliation:
Department of Aircraft Engine Theory, Samara National Research University, 34 Moskovskoe Highway, Samara, Russian Federation
Keyword(s):
Aircraft Engine, Turbine Cooling, Cooled Blades, Cooling Efficiency Coefficient.
Abstract:
An increase in the temperature of the gases forces the cooling system of the turbine blades to become more and more complex. The presented article describes a complex and computer-intensive numerical model of a working blade of a modern high-pressure turbine of a civil aviation aircraft gas turbine engine, which includes a flow region, a blade body, internal cooling channels and coolant supply channels. Using this model, the thermal state of the blade was determined and potential problem areas were found: hot gas leakage, coolant stagnation and overheating. Based on the analysis, several options were proposed for changing the configuration of the internal channels of the blade, which reduce the negative effects found. Although the proposed design options did not fully achieve all the requirements for the blade, they made it possible to find promising ways for further improvement. Also, the authors have practically worked out conjugate numerical models to study the thermal state of th
e turbine.
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