#Csim scilab pdf#

Based on this objective, the proposal was the study of two combustors, one of low-emission based on references and the other designed using a simple thermal cycle of gas turbines.

#Csim scilab pdf#

This work aims for the numerical study of gas turbine combustors using the computational tool ANSYS® WorkbenchTM, having as a proposal an approach of using the k-ω SST model combined with the steady flamelet PDF model with treatment of radiation by the DO model. By the end, the stability condition of the system was verified by analyzing the poles and the Bode diagrams, concluding that the model is unstable for high periods of simulation, factor the explains the reason why the fuel consumption, in small rockets, takes short times During a second phase, the equations were linearized to form a linear system with constant coefficients, defining the transfer functions for degree inputs and representing the system into state space. It was also presented the main parameters for simulation, majorly based on M8 rockets. Consequently, the differential equations were obtained, composing the nonlinear mathematical model and applicable to the hypothesis and simplified considerations adopted. Thus, studies were made about the rocket’s burning chamber (supported on thermodynamics theories), external air flow conditions over the rocket structure (supported on fluid mechanics) and, finally, the rocket dynamics and its trajectory (based on free body diagram and the Theorem of Motion of the Barycenter). This paper studies a model for a variable mass rocket that would describe a curve trajectory from a established inclination, the modeling of the mechanical system was initiated from a single study based on the main structures and the application of the corresponding concepts.