# Aviadvigatel PD-14

The Aviadvigatel PD-14 (previously known as PS-12) is a high-bypass turbofan that was developed by Aviadvigatel to power the Yakovlev MC-21 twin-jet airliner. It is a 14 tf (30,865 lbf) thrust powerplant.

## Development

In December 2009, the PD-14 was developed to be 15% more efficient than its PS-90A2 predecessor and to be installed on the MC-21 and the Ilyushin Il-276.
The PD-14 was announced in early 2010 with its development cost estimated at RUB 35 billion (US$1.1 billion). In April 2010, Aviadvigatel was expecting to start its certification procedure in 2012. Its core was first tested on 26 November 2010. It was displayed for the first time at the 2013 MAKS air show.
Flight tests began in 2015 on an Ilyushin Il-76. Between December 2016 and May 2017, the PD-14 operational performance and working efficiency at all altitudes and speeds were assessed on the Il-76 testbed aircraft at Gromov Flight Research Institute near Moscow. After two years exploring performance at most altitudes, airspeeds and operating modes, the first and second testing stages confirmed its basic operating parameters. A third phase of flight tests debuted in January 2018 from the GFRI Zhukovsky Airfield, conducted in co-operation with certification specialists to formally confirm the pre-certification efforts findings.
Ground tests will continue in parallel, and United Engine Corporation claims that the engine matches the performance of products from foreign competitors and surpasses them for noise and emissions. Bird strike tests on the fan, including high-speed video and vibration measurements, were conducted together with fan blade strength tests. The successful results are expected to reduce the time and cost of attaining full certification status.
United Engine was to deliver five PD-14s to Irkut by the end of 2018, and after Rosaviatsia certification, to start flight tests on the MC-21 in 2019 for type certification of the variant in 2021. EASA certification is expected when it will enter series production. In October 2018, Rosaviatsia granted certification to the PD-14, and deliveries of the first engines for two MC-21s were expected by the end of 2018. European certificate validation was planned for 2019.
In January 2020, Irkut received the first PD-14 engines to be installed on the MC-21 airliner, and the first PD-14-powered MC-21-310 made its maiden flight on 15 December 2020 from Irkutsk.
In October 2021, the engine successfully passed landmark volcanic ash exposure tests. According to Anatoly Serdyukov, the thrust of the PD-14 “practically did not decrease” after the engine was exposed to the presence of the ash for 1 hour.
The first mass-produced batch was delivered to test facility in 2025. Features hollow titanium fan blades for reduced weight and incorporates 16 key technologies, including new materials, coatings, and new design solutions. It was previously approved for low-temperature operation.

## Design

The 1.9 m (75 in) fan has 18 titanium alloy blades, providing an 8.5:1 bypass ratio significantly improved from previous Russian engines, but below the CFM LEAP's 10:1 or the Pratt & Whitney PW1000G's 12:1 for the MC-21 from 2017. The 3D aerodynamics shaped first high-pressure turbine stage has advanced cooling channels. Twenty new materials were developed for the powerplant, including monocrystalline alloys for vanes, and high-strength nickel and titanium alloys for shafts and disks.
Developed from the PS-12 (an uprated PS-90A), the 122–153 kN (27,500-34,500 lbf) thrust powerplant is designed by Aviadvigatel and manufactured by the Perm Engine Company. The two-shaft turbofan has a high-pressure core from the PS-12 with an eight-stage compressor and a two-stage turbine, and four low-pressure stages. The high-bypass engine does not employ an exhaust mixer, fuel burn should be reduced by 10–15% from the CFM International CFM56 and it could power an upgraded Tupolev Tu-204.

## Proposed derivatives

* PD-8V turboshaft 6.8 7.68 – 9680 shp for Mi-24/35 8/17 and other medium heavy heli.
* PD-10 is a derated model for the SSJ-130 at 10.9 tf (24,000 lbf).
* PD-12V: turboshaft variant for the Mil Mi-26 heavy lift helicopter, development started in 2016, 11,500 shp (up to 14,500 shp).
* PD-14А, derated modification of the engine to 12.5 tf (27,600 lbf) for Yakovlev МС-21-200, also it could replace 12 tf Soloviev D-30 powering the Beriev A-40 aircraft.
* PD-14M, uprated to 15.6 tf (34,400 lbf), and PD-16, uprated to 17.5 tf (38,600 lbf), with more LP compressor and turbine stages, for the Yakovlev МС-21-400 stretch to 230-seat and its long-range derivative with a 0.526 lb/lbf/h (14.9 g/kN/s) cruise Thrust-specific fuel consumption; and could replace the 16-tf PS-90A powering the Tupolev Tu-204/214 narrowbody, the Ilyushin Il-96-300 widebody, and the Il-76M-90A freighter.
* PD-18R geared turbofan, 18.7 tf (41,000 lbf), it could reach a cruise Thrust-specific fuel consumption of 0.506 lb/lbf/h (14.3 g/kN/s) and could replace the 17.4 tf (38,000 lbf) PS-90A1 on the Il-96-400T freighter.

### PD-8

PD-8 is a derated model at 78 kN (17,500 lbf) for the SSJ-100, Beriev Be-200, and Ilyushin Il-212. As of mid-2022, a PD-8 prototype had successfully completed ground testing, and had conducted its first flight test installed on an Ilyushin Il-76 aircraft. As of mid-2024, the engine manufacturer was implementing a strategy of using a computer model of the PD-8 for testing in order to reduce the number of required real engine tests, so as to accelerate PD-8 certification.
In February 2025, Vladimir Artjakov of Rostec stated that PD-8 engines had been delivered to the production site of the SSJ100 in Komsomolsk and that flight testing of the new engine was to begin as soon as possible. At March 17th, 2025 the maiden flight of PD-8 under a modified SSJ-100 has been performed.

### PD-35

Launched in the summer of 2016 by United Engine Corporation through Aviadvigatel and NPO Saturn, the 35 tf (77,000 lbf) thrust PD-35 was to be developed until 2025 for 180 billion rubles ($3 billion) including 60 billion for test benches and laboratory equipment, to power future wide-body aircraft including the since-shelved Russo-Chinese CRAIC CR929. The 8 m (26 ft) long engine will weigh 8 t (18,000 lb), its fan was planned to be 3.1 m (10 ft) in diameter and its scaled up PD-14 core to have a nine-stage high-pressure compressor and two-stage turbine.
On 19 January 2018, the Russian government awarded UEC-Aviadvigatel a ₽64.3 billion ($1.13 billion) contract to develop a PD-35-1 demonstrator by 2023, including wide-chord composite fan blades and fan case, a 23:1 compressor pressure ratio, ceramic matrix composites – silicon carbide-silicon carbide (SiC-SiC) and carbon-silicon carbide (C-SiC) – and advanced cooling for 1,450 °C (2,640 °F) temperatures. It could power the Ilyushin IL-96-400, the Il-76 airlifter, Il-78 tanker and an Antonov An-124 replacement Ilyushin Il-106 PAK VTA. A de-rated version would meet the An-124 thrust requirements.
At the end of 2022, the PD-35 was postponed until at least 2029.

## Applications

* PD-8: SJ-100, Beriev Be-200, Ilyushin Il-212
* PD-10: SJ-130
* PD-12V: Mil Mi-26
* PD-14: Yakovlev MC-21, Ilyushin Il-276
* PD-35 : CRAIC CR929, Ilyushin Il-96, Ilyushin Il-106 PAK VTA

## Specifications

The PD-14 Engine and Advanced Engines Family :
| Model | PD-8 | PD-10 | PD-14A | PD-14 | PD-14M | PD-35 |
| Configuration | Twin-spool high bypass turbofan | Twin-spool high bypass turbofan | Twin-spool high bypass turbofan | Twin-spool high bypass turbofan | Twin-spool high bypass turbofan | Twin-spool high bypass turbofan |
| Take-off thrust | 78 kN; 18,000 lbf | 107 kN; 24,000 lbf | 123 kN; 28,000 lbf | 137 kN; 31,000 lbf | 153 kN; 34,000 lbf | 343 kN; 77,000 lbf |
| Dry weight | | 2,350 kg (5,180 lb) | 2,870 kg (6,330 lb) | 2,870 kg (6,330 lb) | 2,970 kg (6,550 lb) | 8,000 kg (18,000 lb) |
| Fan diameter | | 1,677 mm (66.0 in) | 1,900 mm (75 in) | 1,900 mm (75 in) | 1,900 mm (75 in) | 3,100 mm (120 in) |
| Compressor | | 1 fan + 1 LP + 8 HP | 1 fan + 3-stage LP + 8-stage HP | 1 fan + 3-stage LP + 8-stage HP | 1 fan + 4 LP + 8 HP | |
| Combustor | Annular | Annular | Annular | Annular | Annular | Annular |
| Turbine | | 2 HP + 5 LP | 2-stage HP + 6-stage LP | 2-stage HP + 6-stage LP | 2-stage HP + 6-stage LP | |
| BPR | | | 8.6 | 8.5 | 7.2 | |
| OPR | | | 38 | 41 | 46 | |
| TSFC | | 14.9 g/kN/s; 0.526 lb/lbf/h in cruise | 14.9 g/kN/s; 0.526 lb/lbf/h in cruise | 14.9 g/kN/s; 0.526 lb/lbf/h in cruise | 14.9 g/kN/s; 0.526 lb/lbf/h in cruise | |
| Thrust-to-weight ratio | | 4.64 | 4.36 | 4.88 | 5.25 | |
| Application | SSJ-New | Superjet 130 | МС-21-200 | MC-21-310 | MC-21-400 | Comac C929 |