ODK engineers explained how the PD-14 managed to simultaneously reduce the weight and aerodynamic drag of the power plant, as well as increase its reliability, through various solutions. The engine design incorporated a reduced temperature at the combustor outlet, an optimized gas generator, and a gearless scheme.
Another design element is a smaller fan diameter. A compact fan allows for a reduction in engine weight and simultaneously reduces the frontal drag of the nacelle. As a result, not only the engine itself benefits, but the entire aircraft power plant.
Engineers also optimized the dimensions of the gas generator. This simplifies air bleed from the compressor for various onboard systems and allows for a reduction in installation thrust losses.
A separate solution concerns the fan pressure ratio. Its calculated level allowed for the elimination of a variable outer bypass nozzle. This is another way to reduce the weight and drag of the propulsion system without complicating its design with an additional mechanism.
At the same time, the PD-14 retained its classic gearless scheme. The fan is directly connected to the shaft, without a separate gearbox. This option allows for maintaining the necessary balance between weight, service life, reliability, and maintenance costs.
The PD-14 is a two-spool, two-shaft turbofan engine with separate bypass and core flows, a thrust reverser, and a noise suppression system. The power plant is designed for the medium-haul MC-21.