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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.
Main Advantages of PD Engines
High reliability
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.
Besides, the technologies developed within the PD-14 Engine Program are planned to be used to make IGTs for GT Compressor and Generator Packages rated at 8 and 16 MW.
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.
PD-14 Engine Program Design and Development Activities Status
- Detailed design completed with positive conclusions received;
- Engine/ aircraft integration activities launched with Irkut Corporation;
- Extensive testing of engine development components and systems performed at special test rigs;
- Demo engine of the baseline engine design developed in order to demonstrate the PD-14 engine components operational capability;
- The first stage of the engine core development testing completed;
- Availability of critical technologies demonstrated by technology demonstrator engine manufacturing and testing;
- Nacelle components made of polymer composites tested on the prototype engine;
- Detailed design documentation issued for a development batch of PD-14 engines and nacelles;
- Production cooperation to make a development batch of PD-14 engines and nacelles formed and manufacturing launched;
- 100-03 and 100-04 demo engines test program completed with the selected engineering solutions validated;
- Application to the Interstate Aviation Committee Aviation Register to obtain the engine airworthiness certificate filed;
- PD-14 engine certification basis covering IAC AR, EASA, FAA requirements developed;
- PD-14 engine mockup commission held and IAC AR mockup commission protocol approved;
- PD-14 engine-powered МС-21 aircraft mockup commission held and IAC AR mockup commission protocol approved;
- Production preparation performed and Level VI technological availability achieved for manufacturing of the development batch of PD-14 engines;
- Flying testbed preparation for PD-14 engine flight tests is underway.
- PD-14 engine flight testing at IL-76LL flying testbed is underway in the Flight Research Institute named after Gromov.
http://www.avid.ru/en/pd14/
