The PD-8 engine features a supersonic high-pressure turbine stage, for which a pressure reduction ratio of 4 is claimed. This is one of the new technical solutions first applied in the engine's design, and it allows for reduced turbine losses and lower specific fuel consumption. Representatives of ODK shared details about the design innovations and the unit's operating scheme.

The essence of the solution is that the gas flow in this stage accelerates to supersonic speed, after which its pressure sharply decreases. A value of 4 means that the pressure at the stage outlet is approximately four times lower than at the inlet.

For an aviation turbine, this is an important parameter: the more efficiently the hot gas energy is converted into rotor rotation, the less energy needs to be compensated by additional fuel consumption.

The effect is complemented by minimal radial clearances between the rotating and stationary elements of the turbine. The less space for gas leakage around the working blades, the more efficiently the flow energy is used. As a result, the PD-8 achieves a more efficient gas-dynamic scheme with relatively compact engine dimensions.

The technological solution has already been tested not only in calculated modes. During the PD-8 certification program, a full range of tests was completed, including operation in icing conditions, hail, water, and bird ingestion; total operating time exceeded 6500 hours.