NPO Saturn AL-55

The design comprises five main features. It has a three-stage low pressure compressor, five stage high pressure chamber, an annular combustion chamber and a single stage high and low pressure turbines.

In August 2005, the Russian export organization known as Rosoboronexport and India's Hindustan Aeronautics Limited (HAL) signed an agreement for the licensed production of up to 1,000 AL-55I engines. The agreement includes a firm order for 250 engines to be manufactured at HAL facilities in India, to power both HAL HJT-36 trainer and HAL HJT 39 combat trainer aircraft.

AL-55

AL-55/I: A variant designed for licensed production in India.

• HAL HJT-36 Sitara
• HAL HJT 39
• Mikoyan MiG-AT[1]
• KB SAT SR-10

Data from UEC Saturn.[2]

General characteristics

• Type: Double spool (two shaft) turbofan
• Length: 1,950 mm (76.77 in)
• Diameter: 590 mm (23.23 in)
• Dry weight: 315 kg

Components

• Compressor: two-spool, with 3-stage low-pressure (LP) and 5-stage high-pressure (HP) and one annular compressor
• Turbine: 1 LP stage and 1 HP stage

Performance

• Maximum thrust: 1,760 kgf (17.3 kN; 3,900 lbf) (take-off thrust)
• Overall pressure ratio: 17.5
• Bypass ratio: 0.515
• Air mass flow: 28.5 kg/s
• Turbine inlet temperature: 1445 Tc[3][4][5]
• Specific fuel consumption: 0.69 kg/kgf.h (Specific fuel rate at the limiting point), 0.645 kg/kgf.h (Specific fuel rate in cruising mode)[3][4][5]
• Thrust-to-weight ratio: 5.59 (take-off thrust)

• List of aircraft engines