Modelling of Variables Gas Properties and Compositions in Turbomachinery Flow Simulations
This paper describes the formulation of computational methods for aerothermodynamic predictions in turbomachinery passages and gas-turbine engine components accounting for changes in fluid properties. The changes accounted for include the change of specific heats with temperature and changes in composition as consequence of the injection of chemical compounds different from those forming the main gas stream, and the reactions between the main gas stream and these compounds. The flow equations for compressible flow with variable properties and compositions are stated, with particular reference to the inviscid flux jacobians and their eigenvalues and eigenvectors. These are used to derive a Roe-like flux difference splitting algorithm. The algorithm derived is applied to the computation of variable property, reacting flow in a transonic nozzle and to the computation of equilibrium flow in a High-Pressure turbine stage.