Wikipedia

Progress AI-22

The Progress AI-22 is a turbofan engine, developed by ZMKB Progress, Motor Sich JSC, KMPO and KAPO.

Progress AI-22
Type Turbofan
National origin Ukraine, Russia
Manufacturer ZMKB Progress,[1] Motor Sich JSC,[1] KMPO,[1] KAPO[1]
First run September 26, 2000[2]
Developed from DV-2[2]
Developed into AI-222[3]

Development

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The AI-22 was developed in the 1990s and is designed for the Tupolev Tu-324 regional airliner.[1]

The engine is based on a gas generator version of the DV-2 engine.[2] It has a modular design consisting of 10 modules.[2] Materials and special coatings of parts allow the engine to operate in various climatic conditions.[2]

A successful start of a full-size engine was made on September 26, 2000.[2] Further development of the engine is suspended indefinitely.

Organisation

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The AI-22 is created in a cooperation of four enterprises:

  • ZMKB Progress is tasked with the manufacturing of external piping and cabling.[1] It also conducts tests and performs the final assembly of the engine.[1]
  • Motor Sich JSC is tasked with the manufacturing of the high-pressure compressor, combustion chamber, high-pressure turbine, air starter, air separator, start valve, air bypass valve, parts for piping, and fasteners used in the assembly of the engine.[1]
  • KMPO is tasked with the manufacturing of the low-pressure compressor and fan, the low-pressure turbine, middle and rear support, transmission units, engine mountings, and oil system units.
  • KAPO is tasked with the manufacturing of the thrust reverser, jet nozzle, and cowlings.[1]

Emissions

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The specific emissions of the engine during the landing and takeoff cycle are as follows:

  • CO = 110 g/kN[1]
  • HC = 12 g/kN[1]
  • NOx = 45 g/kN[1]
  • SN = 20 g/kN[1]

Applications

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Specifications (AI-22)

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Data from ivchenko-progress.com,[4][2] aviaros.narod.ru[3] and trade.tatcenter.ru[1]

General characteristics

  • Type: Two-spool turbofan engine
  • Length: 3,060 mm (120 in)[1]
  • Diameter: 1,020 mm (40 in)[1] (fan)
  • Dry weight: 765 kg (1,687 lb)[1]

Components

Performance

  • Maximum thrust:
    • 4,340 kgf (42.6 kN; 9,600 lbf)[4] in maximum emergency mode
    • 3,820 kgf (37.5 kN; 8,400 lbf)[4] in takeoff mode
    • 840 kgf (8.2 kN; 1,900 lbf)[4] in maximum cruising mode
    • 775 kgf (7.60 kN; 1,710 lbf)[4] in cruising mode
  • Overall pressure ratio:
    • 15.49[1] in takeoff mode
    • 19.16[1] in cruising mode
  • Bypass ratio:
    • 4.94[1] in takeoff mode
    • 4.57[1] in cruising mode
  • Air mass flow:
    • 125.85 kg/s (277.5 lb/s)[1] in takeoff mode
    • 45.6 kg/s (101 lb/s)[1] in cruising mode
  • Turbine inlet temperature:
    • 1,450 °C (2,640 °F)[1] in takeoff mode
    • 1,249 °C (2,280 °F)[1] in cruising mode
  • Specific fuel consumption: 0.63 kg/(kgf⋅h)[1] in cruising mode

See also

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Related lists

References

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  1. ^ a b c d e f g h i j k l m n o p q r s t u v w x y z "AI-22 engine". trade.tatcenter.ru. Archived from the original on 2009-07-13. Retrieved 2 November 2021.
  2. ^ a b c d e f g h i j k l "More about the AI-22 gas turbine engine". ivchenko-progress.com. Ivchenko-Progress. Archived from the original on 2012-05-12. Retrieved 15 October 2021.
  3. ^ a b c "AI-22". aviaros.narod.ru. Retrieved 21 October 2021.
  4. ^ a b c d e "Aircraft turbojet bypass engine AI-22". ivchenko-progress.com. Ivchenko-Progress. Archived from the original on 2012-05-29. Retrieved 15 October 2021.
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