Progress AI-22

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

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.

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

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

• CO = 110 g/kN¹
• HC = 12 g/kN¹
• NOx = 45 g/kN¹
• SN = 20 g/kN¹

• Tupolev Tu-324² (proposed)
• Yakovlev Yak-48² (proposed)

Data from ivchenko-progress.com,⁴² aviaros.narod.ru³ and trade.tatcenter.ru¹

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 + 7HP²
• Combustors: Annular with 16 nozzles²
• Turbine: 1HP + 3LP²
• Fuel type: T-1, TS-1 or RT kerosene type fuel³

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:
  
  • 15.49¹ in takeoff mode
  • 19.16¹ in cruising mode
• Bypass ratio:
  
  • 4.94¹ in takeoff mode
  • 4.57¹ 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