Muravchenko O. Investigation of Operation of Compressor of Aviation Gas-Turbine Engine at Reduced Rotational Speeds

In this work the method of testing calculation of axial-symmetric flow in the multistage compressor is proposed. This method permits to determine the flow radial structure and compressor sum performances. The possibility of compressor parameters calculation at open by-pass valves position is the particular feature of this method.The approbation of the method was fulfilled for the low pressure compressor (LPC) of D-27 engine due to comparison of obtained results with the test data. Two-dimensional mathematical model of flow in the D-336 engine LPC was created. Three variants of modification of geometrical parameters of D-336 engine compressor were proposed for adaptation of the compressor to the ground operation conditions. These modifications are directed to the increasing of the compressor operation efficiency while conserving the sufficient stable operation margins at reduced rotational speeds.