NPO Saturn AL-55
| NPO Saturn AL-55 | |
|---|---|
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| The Jet engine AL-55 (The international aerospace salon MAKS-2011) | |
| Type | Turbofan |
| National origin | Russia |
| Manufacturer | NPO Saturn and serial broduction by Ufa Engine Industrial Association JSC |
| Major applications | Originally designed for HAL HJT-36 Sitara |
| Program cost | Estimated more than US$ 640 million |
| Unit cost | USD$1.3 million |
The NPO Saturn AL-55 is a high performance turbofan engine manufactured by NPO Saturn Russia, for powering advanced trainers, unmanned aerial vehicles (UAV) and light attack aircraft. The AL-55I is a variant of the engine which powers the HAL HJT-36 Sitara Indian jet trainer.
Design
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.
Variants
- AL-55
- AL-55I: A variant designed for licensed production in India.
Applications
Specifications
Data from [2]
General characteristics
- Type: Double circuit turbofan
- Length: 1950 mm (76.77165 in)
- Diameter: 590mm (23.2283 in)
- Dry weight:
Components
- Compressor: two-spool, with low-pressure (LP) and high-pressure (HP) and one annular compressor
- LP compressor with 3 fan stages
- HP compressor with 5 stages
- Turbine: 1 LP stage and 1 HP stage
Performance
- Maximum thrust: 1,760kgf (Take-off thrust)(17.26 kN)
- 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]
- Power-to-weight ratio:
Engine cycle
- Airflow: 28.5 kg/c
- Bypass ratio: 0.515
- Overall pressure ratio: 17.5
- Turbine entry temperature: 1445 Tc[3][4][5]
See also
References
- ↑ MiG-AT aircraft
- ↑ "Engines for military aircraft and UAS AL-55".
- 1 2 http://www.russia-algeria.ru/3/Saturn_english_2010.pdf
- 1 2 "United Engine Corporation". Uk-odk.ru. Retrieved 2014-04-06.
- 1 2 Соколов Константин. "NPO "SATURN" > AL-55". Npo-saturn.ru. Retrieved 2014-04-06.
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