Optimum design of the turbine blisk of a mini-turbojet engine

As the main parts of rotor of aero-gas turbine engine, due to arduous working conditions, the design of turbine as well as compressor disks is of importance. These disks are loaded under centrifugal and thermal forces which gets higher with increasing rotating speed, and the gas’s pressure and temperature. To improve the rotor dynamic behavior, decrease the bearing’s load and motor’s weight, the weight of the rotor, as the main part of the motor, should be minimized. Rotating speed, high temperature working condition, high temperature gradient, and the demand for minimum weight, imply serious restrictions on the design of rotor, especially turbine’s rotor. On the other hand, the strength analysis is prior to the study of rotor’s life because, to assess the cyclic loading, first the static one should be investigated. The aim of this study is to optimum the weight of a turbine integrally bladed disk (blisk) of a mini-turbojet engine. Aero-thermodynamic design parameters such as geometry, blades’ number and location, aerodynamic loads’ distribution, temperature and pressure distribution on the rotor, and rotating speed are the input parameters of the optimum design problem of the rotor’s disk under strength and geometrical constraints. To do so, numerical programs for design, analysis and optimization of the disk is developed and the obtained results are validated through previous ones in the literature. In addition, the structure of a special mini-turbojet engine is designed in an optimum manner.