MDO of Gas Turbine Engines

摘要

A gas turbine engine which is an extremely complicated system mainly consists of a compressor, aturbine, and a combustion chamber. The design of it involves many disciplines such as computationalfluid dynamics (CFD), heat conduction, structural design and computational solid mechanics (CSM)and some of these disciplines interact from each other strongly. The high performance of theadvanced gas turbine engine requires that these disciplinary design should be integrated somultidisciplinary design optimization (MDO) is vitally important for the next generation gas turbineengines. The procedure of multidisciplinary design optimization (MDO) for gas turbine engine wasinvestigated in the present paper. In CDF, the Navier-Stokes equations are solved to get the flow field.For the design of a blade, quasi-three dimensional calculation which was composed of the iterationbetween the stream function calculations on a mean S_2 stream surface and several S_1 stream surfaceof revolution for transonic flow was employed and in the structural design of a blade, the controlleddiffusion airfoils (CDA) technique was adopted to get the airfoil of a blade. In the heat conductionanalysis, FEM was used to solve the Poisson’s equation. In CSM, FEM was used to carry out theanalysis of stress and vibrations. The multidisciplinary interface technique was investigated. Thegoal of MDO of gas turbine engine is to increase the performances and to reduce weight. In order toachieve this goal, optimization mathematics model including the selection of design valuables, theconstruction of the objective and constraint functions is also investigated. In the end of the paperseveral numerical examples are presented which indicated that this procedure is very efficient.