The Turbomeca TM 333 is a turboshaft engine manufactured by French company Turbomeca and designed for helicopters weighing 4-5 tonnes. It first ran in August 1981 and was introduced commercially in the mid-1980s. It was the first Turbomeca engine to use a single stage turbine, making it more compact than its predecessors. In its original design, the engine was rated at 750 continuous horsepower, though it was designed to allow for future power increases, and the later 2B2 variant made 1,100 horsepower.
|Major applications||HAL Dhruv|
Specifications (TM 333 2M2)Edit
Data from EASA TCDS E.030 TM333 Series Issue 05 
- Type: Twin-spool turboshaft
- Length: 1,045 mm (41.1 in)
- Diameter: 454 mm (17.9 in) (width), 745 mm (29.3 in) (height)
- Dry weight: 162.5 kg (358.3 lb)
- Compressor: Two-stage axial, single-stage centrifugal
- Combustors: Annular,reverse flow
- Turbine: Single-stage compressor turbine, single-stage power turbine
- Maximum power output: 736 kW (987 shp) (maximum continuous)
- Power-to-weight ratio:
- "TM.333; a new generation turboshaft" (PDF). Flight International. 1 January 1983. Retrieved 13 April 2017.
- "Military engines: Local power". Flightglobal. 1 May 2007. Retrieved 13 April 2017.
- "Gaining altitude". Flightglobal. 21 February 2006. Retrieved 13 April 2017.
- EASA E.030 www.easa.europa.eu - Retrieved: 7 December 2021
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