A New Method of Conceptual Design of the Flow Part of a Gas Turbine Engine

Flow path design is the main content in the preliminary design of the engine. This article uses a certain type of turbofan engine as a reference. On the premise of ensuring that the thermodynamic state parameters of each component are constant, the high-pressure turbine and high-pressure compressor are designed with the starting point of reducing the number of high-pressure turbine stages. Redesign of flow path in cruising state. The results show that although the number of high-pressure turbine stages is reduced, the calculated flow path still has a high match with the original flow path. For the high-pressure compressor, the overall axial length is smaller than the actual value. Since the axial clearance of the blades at each stage is too small, the relative speed ratio and absolute speed ratio are at the minimum boundary value. From the current results alone, although the reduction in the number of high-pressure turbine stages has been achieved, the high-pressure compressor needs to solve the current problems by increasing the number of stages. Only from the perspective of flow path geometric parameters, the calculation results of the high-pressure turbine and compressor can maintain good consistency with the original structure.