Design of a High Temperature Turbine Rotor Air CoolingB. Zweig, O. Ophir, F. Roizner, O. Dobrilko. B. Nemirovski, E. EntinM.Shapira, A.Levy, R.Payevsky, M. Harel
This project deals with an educational scheme concerning design of the cooling method of a turbojet engine turbine rotor of. The project was a cooperation between the faculty of Aerospace Engineering of the Technion and Bet Shemesh Engines Ltd (BSEL hereafter) and was conducted as part of the final year design project for undergraduate students.
The TSFC, meaning the amount of fuel required per unit of thrust, is a parameter indicating the efficiency of a jet engine. The TSFC depends on the TIT and the air pressure ratio. Each TIT has its optimal compression ratio for which maximal TSFC is achieved. Increasing TIT results in increasing the optimal compression ratio.
Therefore designers wishing to increase turbojet efficiency focused on increasing the TIT. However the turbines rotors alloys cannot withstand operation at very high temperatures. This lead to the use of methods to cool the said rotors. These methods typically require using some of the relatively cool compressed air at the combustor entry to cool the rotors.
This project intent was to design the cooling of an existing turbojet engine rotor to allow higher TIT and increased power.