Analysis of the bearing nodes loads of turbine engine at an unmanned helicopter during a jump up and jump down maneuver

Analysis of the operating load of foil-air bearings in the gas generator of the turbine engine during the acceleration and deceleration maneuver

“…In the maneuver jump up and jump down [16] this force was omitted, in this case is one of significant value. With respect to the radial forces, during the maneuver jump-up and jump-down radial bearing A is more loaded than the bearing B and the maximum value of the loading force radial bearings (bearing node A) is P p = 17.1 N.…”

“…In the case of the FSTC-1 turbine engine, designed at the Department of Thermodynamics, Fluid Mechanics and Aviation Propulsion Systems of Lublin University of Technology, it is important to determine the status of the loading of bearings nodes, especially those of gas bearings (transverse and axial) on which the gas generator operates. The jump-up and jump-down maneuver is described in [16]. The study of the maximum loads on bearing nodes of the drive unit shows that during the jump-up and jump-down maneuver the maximum loading force acting on radial bearings is P p = 17.1 N and the force acting on axial bearings resets, given the working components of the gas generator are designed so that axial aerodynamic forces they create could balance each other.…”

“…All components of gas generator set have been described and parameterized in [16]. Difficult operating conditions (high rotation speeds, high temperatures, difficult access), in the case of gas bearings are acceptable [11,13,15].…”

“…According to developed in [16] states model of the operating load for the foil-air bearings of the engine, which is the subject of research, we can mention the following forces acting on the radial bearing of the rotor set:…”

CFD Analysis of Charge Exchange in an Aircraft Opposed-Piston Diesel Engine

“…Compression-ignition engines are not widely used in aviation as this sector is dominated by jet turbine engines and turboshaft engines: the main reason is the relatively high power-to-weight ratio [1,2,3,4]. In the 1940s, when aircraft compression-ignition engines began to be developed, turbojet and turboprop engines appeared and successfully satisfied the contemporary demands of aviation.…”