avia.wikisort.org - Engine

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

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

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

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

• Tupolev Tu-324[2] (proposed)
• Yakovlev Yak-48[2] (proposed)

Specifications (AI-22)

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

• Compressor: Fan & 5LP + 7HP[2]
• Combustors: Annular with 16 nozzles[2]
• Turbine: 1HP + 3LP[2]
• Fuel type: T-1, TS-1 or RT kerosene type fuel[3]

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
• Power-to-weight ratio:

See also

Related lists

• List of aircraft engines

References

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