|Progress propfan on the Antonov An-70|
|Manufacturer||Ivchenko-Progress , NPC Saljut and Aerosila (AV/SV-27 Propeller)|
|Major applications||Antonov An-70|
|Developed from||Lotarev D-36|
The Progress D-27 is a three-shaft propfan engine developed by Ivchenko Progress. The gas generator was designed using experience from the D-36 turbofan. The D-27 engine was designed to power more-efficient passenger aircraft such as the abandoned Yak-46 project and it was chosen for the An-70 military transport aircraft.
Design and development
The engine was developed by the Ivchenko-Progress Design Bureau for commercial and military transport aircraft. It was designed to meet the expected growth in demand for new aero engines for civil and military applications. It has a take-off rating of 13,240 ehp for the Antonov An-70. Gunston lists ratings between 13,880 and 16,250 hp for the engine. The engine prototype was flight-tested using the Gromov Flight Research Institute Il-76LL flying test-bed.
Ivchenko-Progress also proposed derivatives based on the D-27 engine core. Proposals included:
- AI-127 - a turboshaft with a rated power of 14,500 hp for the Mil Mi-26 helicopter.
- AI-727 - a range of ultra-high bypass geared turbofan engines with a low-noise, wide-chord, fan and thrust between 9,000 and 11,000 kgf.
The D-27’s three-shaft gas turbine engine has an axial low-pressure compressor, a mixed-flow high-pressure compressor, an annular combustion chamber, a single-stage high-pressure turbine, and a single-stage low-pressure turbine. The SV-27 contra-rotating propfan, provided by SPE Aerosila, is driven by a four-stage turbine via a shaft connected to a planetary reduction gear which incorporates a thrust meter. The front propeller has eight blades, and the back propeller has six blades.
- Type: Three-shaft propfan engine
- Length: 4.2 m (165.3 in)
- Width: 1.2 m (49.5 in)
- Height: 1.3 m (53.9 in)
- Propeller diameter: 4.5 m (177.1 in)
- Dry weight: 1,650 kilograms (3,638 lb)
- Compressor: Low-pressure five-stage, axial flow and high-pressure 2 axial and single centrifugal stages 
- Combustors: Annular combustion chamber
- Turbine: Single-stage high-pressure, single-stage low-pressure
- Maximum power output: 14,000 horsepower (10,440 kW)
- Power-to-weight ratio: 6.33 kW/kg (3.85 hp/lb)
- Allison 578-DX
- Europrop TP400
- General Electric GE-36 UDF
- Kuznetsov NK-12
- Rolls-Royce RB3011
- Pratt & Whitney/Allison 578-DX
- Russia, Central/Eastern Europe and China Turbofan and Turbojet Engines, Forecast international[permanent dead link]
- "The Development of Jet and Turbine Aero Engines" 4th edition, Bill Gunston 2006, Patrick Stephens, ISBN 0 7509 4477 3 p.211
- "More detailed information about D-27 engine". Archived from the original on 2013-01-26. Retrieved 2012-06-29.
- D-27 at deagel.com
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