الفهرس 
Turbojet Engine (Jet Cat P200) Thermodynamic Cycle AnalysisOnly 14 pages are availabe for public view
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Abstract
This study processes the conversion of Micro Turbojet Engine to Micro Turboprop Engine through describing the Aerothermodynamics analysis of both engine cycles and design of a low-pressure single-stage axial flow turbine suitable for driving the propeller using computational methods. The specifications of turbine are based on the typical geometric restrictions and specifications of small gas turbine engine Jet Cat P200. The baseline design parameters such as flow coefficient, stage-loading coefficient are close to 0.95 and 1.04 respectively with maximum flow expansion in the NGV rows. In the preliminary design mode, the mean line approach is used to generate the turbine flow path. While the turbine blades design is achieved by considering three blade sections at hub, mean and tip, using developed code to meet the design constraints based on free vortex law of blading. An average exit swirl angle of less than 5 degrees is achieved leading to minimum losses in the stage. Also, NGV and rotor blade numbers are chosen based on the optimum blade solidity. Detailed design for Free Turbine is introduced which include bearings, gearbox selection and shaft oil system. CFD simulation of air flow through the power free turbine is performed using ANSYS CFX 16.0. The obtained results are used to validate the prediction of the analytical model for the Free Power turbine characteristics curve. Also, the converted Micro Turbojet engine Performance is evaluated.