PD-14  
Initial Operational Capability (IOC): 2019
Total Production: ?
Origin: Russia
Corporations: Aviadvigatel Perm Engine Company*, MMPP Salut, NPO Saturn and UMPO   (*) lead contractor
Parent System: PD-14
Initial Operational Capability (IOC): 2017
Maiden Flight: 2014
Total Production: 70
Family Members: PD-10, PD-12V, PD-14A, PD-14M and PD-18R
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Description: The PD-14, formerly known as the PS-12 and/or PS-14, is a fifth generation civil turbofan engine being developed by Aviadvigatel Perm Motors, a part of United Engine Corporation (UEC), to be one of the alternative power plants to power the MS-21 twin-jet passenger aircraft family. The PD-14 designation was announced in early 2010 with its development cost estimated at 35 billion Russian Rubles ($1.1 billion at that time). By mid-2012 the developmental cost estimation has increased to 70 billion Rubles. The PD-14 program is expected to deliver an engine family ranging from 9 to 18 tons of thrust. The MS-21 airliner equipped with PD-14 engines may enter revenue service by 2017 with the engine to receive certification in 2015-2017.

The PD-14 engine is based on classic double-flow scheme without mixing of internal and external flows and that results in 12 to 16 percent fuel economy, hazardous emission (by 30 to 45 percent lower than CAEP 6) and noise level reduction. Noise requirements will be satisfied with installation of a new second generation noise reduction system and a new fan. The first PD-14 engine demonstrator was assembled by a variety of enterprises part of the UEC on May 30, 2012, and is expected to begin testing in the second half of 2012.

The PD-14 turbofan engine is intended to power the MC-21-200 airliner and will develop 14 tons (31,000-lb) of thrust per engine at takeoff. In June 2012, Russian Technologies became the launch customer for the PD-14 engine powering 35 MC-21 airliners. The PD-14 engine may enter service in 2019 during the testing phase of the MC-21-200 airliner.

PD-14 Applications


Airliners MC-21-200 Propulsion Systems PD-24 PD-7

PD-14 Specifications

Thrust-to-Weight Ratio: 4.88
Dimensions
Fan Diameter: 1.90 meter (75 inch)
Weight
Dry Weight: 2,870 kilogram (6,327 pound)
Max Takeoff Thrust: 31,000 pound (14,062 kilogram)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Operators & Related Equipment


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