Progress AI-22
# Progress AI-22

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

## Development

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

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

A successful start of a full-size engine was made on September 26, 2000. 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. It also conducts tests and performs the final assembly of the engine.
* 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.
* 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.

### Emissions

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

* CO = 110 g/kN
* HC = 12 g/kN
* NOx = 45 g/kN
* SN = 20 g/kN

## Applications

* Tupolev Tu-324 (proposed)
* Yakovlev Yak-48 (proposed)

## Specifications (AI-22)

Data from ivchenko-progress.com, aviaros.narod.ru and trade.tatcenter.ru

**General characteristics**

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

**Components**

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

**Performance**

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