Inlet and Outlet Casings of the Turbojet Engines – Design and Experiment

Abstract

The paper presents special design method for three-dimensional design of the inlet and outlet channels of the turboprop engines. The method is based on the solution of indirect problem in internal aerodynamics, which is realised by mechanical construction of the flow field between inlet and outlet sections of the designed channel. The flow field is represented by number of flow tubes made of special plastic material, of optimised geometrical shape and their course in the space. The method was applied on the design of inlet channel of the three-shaft turboprop engine Walter M 602 and the aircraft L 610 and on the outlet channel of the two-shaft turboprop engine Walter M 601. Both channels have been manufactured and proved excellent aerodynamic properties. The channels have satisfied the airworthiness requirements and have been certified by the Czech Aviation Administration and by Federal Aviation Administration of the U.S.A. as well. The application of the new outlet channel have contributed to considerable improvement of the performance of the engine of more than 3 % at the same absolute fuel consumption and at 5 °C lower temperature of the gases at the inlet section of the turbine. The mass of the new channel is of 1 kg lower than the original one.