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Estimation and Calculus of Turbojet Performances with Optimal Turbine Blades Cooling
Salim Bennoud
Pages - 100 - 110     |    Revised - 01-10-2013     |    Published - 01-11-2013
Volume - 7   Issue - 4    |    Publication Date - November 2013  Table of Contents
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KEYWORDS
Engine Performances, Thermodynamic Turbojet Cycle, Turbine Blades Cooling.
ABSTRACT
The temperature augmentation of the turbine inlet gas will always produce an augmentation of thrust, thus the improving of overall performances of the turbojet. This augmentation will benefit the performance, but this effect has drawbacks because of the produced effects on the turbine blades such as the thermal fatigue, the corrosion and also the creep.

These problems act and influence on the thermal and mechanical characteristics of the material, so the factors of security and cost are affected accordingly. Under these conditions, the turbine blades must be cooled to maintain their integrity and achieve their maximum life period.

The principal objective of this work is to develop a data processing application able to calculate the turbojet performances, as well as the calculation of turbine blades cooling.

The developed application makes the calculation of the turbine blades cooling to different altitudes, and has certain advantages, such as: the possibility to have detailed results, the capacity to work out a report, the total absence of intermediate calculations appearance and a total elimination of the curves and graphs use to get the values of each simulation.
CITED BY (2)  
1 Bennoud, S. Modeling and Simulation of Defects Due to corrosion in Turbine Blades of Turbojet.
2 Bennoud, S., Hocine, S., & Slme, H. Calculus of Turbojet Performances for Ideal Case.
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Associate Professor Salim Bennoud
Faculty of Technology/Laboratory of Aircrafts University of Saad Dahlab Blida,09000 - Algeria
bensalimen2006@yahoo.fr