Progress D-27

D-27
Progress propfan on the Antonov An-70
Type Propfan
National origin Ukraine
Manufacturer Ivchenko-Progress , NPC Saljut and Aerosila (AV/SV-27 Propeller)
First run 1992
Major applications Antonov An-70
Beriev A-42PE
Antonov An-180
Number built 16[1]
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.[2] 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.[3] Gunston[2] 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.

Applications

Specifications (D-27)

Data from forecastinternational.com[1][4]

General characteristics

  • 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)
  • Diameter:
  • Dry weight: 1,650 kilograms (3,638 lb)

Components

  • Compressor: Low-pressure five-stage, axial flow and high-pressure 2 axial and single centrifugal stages [5]
  • Combustors: Annular combustion chamber
  • Turbine: Single-stage high-pressure, single-stage low-pressure

Performance

See also

Comparable engines

Related lists

References

  1. 1 2 Russia, Central/Eastern Europe and China Turbofan and Turbojet Engines, Forecast international
  2. 1 2 "The Development of Jet and Turbine Aero Engines" 4th edition, Bill Gunston 2006, Patrick Stephens, ISBN 0 7509 4477 3 p.211
  3. ↑ http://ivchenko-progress.com/?portfolio=d-27&lang=en
  4. ↑ D-27 at deagel.com
  5. ↑ "Archived copy". Archived from the original on 2013-01-26. Retrieved 2012-06-29. More detailed information about D-27 engine
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.