JETCAT P200 schematic drawing

... start the determination of gas flow parameters at different engine sections, it is assumed that, the engine is working at standard conditions. The total flow parameters at different engine modules are obtained by solving the Continuity, Energy and Momentum equations. Fig. 1 illustrates a schematic drawing for the studied engine. The generated aerodynamic data from this module of the MATLAB code is illustrated in Table 1. The resultant data from this step is used to determine the different dimensionless groups like the mass flow and the specific speed ...

... into cells. The included (ATM optimized) Automatic Topology optimized feature generates a structured hexahedral cell that tracks the surface of the geometry of the blade and is aligned with the direction of the flow. The target number of elements in the mesh is also set. The mesh independence of the flow solutions is checked as shown in Table 5. Fig. 10 shows the structured mesh generated in the rotor domain and nature of the mesh is clearly visible ...

... of the axial turbine stage is reduced into the passage of one stator blade and one rotor blade cascade. This passage works as a sub-domain of the main domain of the whole turbine to reduce the calculations time and data size. The rotor domain rotates at the turbine rotor speed and the stator domain remains stationary. Fig. 12 shows the cascade simulation domains for the turbine CDF model. ...

... pressure conservation, known as a frozen rotor interface. Therefore, frozen rotor interfaces are used between these domains. The inlet boundary conditions are set as the total pressure and total temperature. The outlet is chosen as a static pressure specification. These boundary conditions for the two computational domains are demonstrated in Fig. 13. a, b. As recommended in turbomachinery simulation, the flow is modelled as three dimensional, steady, turbulent, compressible and viscous flow with k-ω turbulence model. Mesh independence study is made to ensure that the results are independent on the mesh intensity, Table 5. Table 5 shows the data of the mesh independent study. ...

... the running specific speed and repeat the previous procedure to generate the off-design performance curves. Fig. 14 shows a set of graphs illustrating the variation of the expansion ratio for the turbine stage with the normalized mass flow rate at different specific speeds generated from both the analytical and the CFD methods. While fig. 15 shows two graphs illustrating the variation of the turbine total-total isentropic efficiency with the turbine ...

... the running specific speed and repeat the previous procedure to generate the off-design performance curves. Fig. 14 shows a set of graphs illustrating the variation of the expansion ratio for the turbine stage with the normalized mass flow rate at different specific speeds generated from both the analytical and the CFD methods. While fig. 15 shows two graphs illustrating the variation of the turbine total-total isentropic efficiency with the turbine stage expansion ratio at the design speed and 60 % specific speed. ...