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The PD-14 Engine
PD Engines based on the common core make a family of Russian bypass two-shaft turbojet engines with an efficient noise suppression system intended for short- and medium-haul aircraft and IGTs.
The main specific feature of the PD engine family is the use of a compact common core and a relatively light shroudless fan.
Key technologies: hollow wide-chord titanium blades, blisks and a weld section in the HP compressor rotor, low emission combustor made of intermetallic alloy, single crystal HP turbine blades with an advanced cooling system, ceramic coating on the hot section components, hollow LP turbine blades, nacelle made of composite materials.
Part number:
Supplier:
United Engine Corporation (UEC)Description
Mean time to engine in-flight shutdown which is not recoverable in flight > 200 000 h
A/C departure reliability related to engine readiness > 99,96 %
Low fuel consumption
Reduced SFC compared to other contemporary engines > 10...15 %
Compliance with upcoming environmental standards
Noise reduction relative to ICAO Stage 4 requirements > 15...20 EpNdB
NOx emission reduction relative to ICAO 2008 requirements > 30 %
Compliance with current certification requirements АП-33, FAR-33, CS-E, ETOPS
Engine Modifications under Development
The family of advanced turbofan engines for short- and medium-haul aircraft comprises the following engines: PD-14, PD-14А, PD-14М, PD-10;
PD-14 – baseline engine for МС-21-300 aircraft;
PD-14А – derated modification of the engine for МС-21-200 aircraft;
PD-14М – uprated modification of the engine for МС-21-400 aircraft;
PD-10 – derated modification of the engine (10...11 ton-force) for SSJ‑NG aircraft.
Competitive Advantages by Operational Cost Efficiency
are achieved through the following specific performance- and design-related features compared to competitors:
Lower combustor exit temperature is a very important factor contributing to cost and risk reduction in reaching the target durability and reliability of the short-cycle A/C engines.
Smaller fan diameter of the PD-14 engine contributes to real engine weight and nacelle drag reduction.
Optimum dimensions of the core duct help resolving the problem of relatively high compressor air bleeds for different purposes and reduce installation thrust losses.
High enough fan design pressure ratio (due to somewhat lower bypass ratio) eliminates the need in the variable fun duct nozzle which inevitably increases engine weight and drag, and reduces installation thrust losses.
Conventional configuration of the PD-14 engine without a gearbox which has been well proven in service enables achieving the target weight, life, reliability and maintenance costs.
Optimum combination of reasonably high cycle parameters and a well proven engine configuration with a direct fan drive provides for lower engine cost, MRO costs, lower powerplant weight and drag and makes the PD-14 engine excel in operational cost efficiency and life cycle cost.
A/C departure reliability related to engine readiness > 99,96 %
Low fuel consumption
Reduced SFC compared to other contemporary engines > 10...15 %
Compliance with upcoming environmental standards
Noise reduction relative to ICAO Stage 4 requirements > 15...20 EpNdB
NOx emission reduction relative to ICAO 2008 requirements > 30 %
Compliance with current certification requirements АП-33, FAR-33, CS-E, ETOPS
Engine Modifications under Development
The family of advanced turbofan engines for short- and medium-haul aircraft comprises the following engines: PD-14, PD-14А, PD-14М, PD-10;
PD-14 – baseline engine for МС-21-300 aircraft;
PD-14А – derated modification of the engine for МС-21-200 aircraft;
PD-14М – uprated modification of the engine for МС-21-400 aircraft;
PD-10 – derated modification of the engine (10...11 ton-force) for SSJ‑NG aircraft.
Competitive Advantages by Operational Cost Efficiency
are achieved through the following specific performance- and design-related features compared to competitors:
Lower combustor exit temperature is a very important factor contributing to cost and risk reduction in reaching the target durability and reliability of the short-cycle A/C engines.
Smaller fan diameter of the PD-14 engine contributes to real engine weight and nacelle drag reduction.
Optimum dimensions of the core duct help resolving the problem of relatively high compressor air bleeds for different purposes and reduce installation thrust losses.
High enough fan design pressure ratio (due to somewhat lower bypass ratio) eliminates the need in the variable fun duct nozzle which inevitably increases engine weight and drag, and reduces installation thrust losses.
Conventional configuration of the PD-14 engine without a gearbox which has been well proven in service enables achieving the target weight, life, reliability and maintenance costs.
Optimum combination of reasonably high cycle parameters and a well proven engine configuration with a direct fan drive provides for lower engine cost, MRO costs, lower powerplant weight and drag and makes the PD-14 engine excel in operational cost efficiency and life cycle cost.