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Turbomeca TM 333 
Summary
The Turbomeca TM 333 is a turboshaft engine manufactured by French company Turbomeca and designed for helicopters weighing 4-5 tonnes.[1] It first ran in August 1981 and was introduced commercially in the mid-1980s.[1] It was the first Turbomeca engine to use a single stage turbine, making it more compact than its predecessors.[1] In its original design, the engine was rated at 750 continuous horsepower, though it was designed to allow for future power increases,[1] and the later 2B2 variant made 1,100 horsepower.[2]
| TM 333 | |
|---|---|
| Type | Turboshaft |
| National origin | France |
| Manufacturer | Turbomeca |
| First run | 1981 |
| Major applications | HAL Dhruv |
Variants edit
Applications edit
Specifications (TM 333 2M2) edit
Data from EASA TCDS E.030 TM333 Series Issue 05 [4]
General characteristics
- 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)
Components
- Compressor: Two-stage axial, single-stage centrifugal
- Combustors: Annular,reverse flow
- Turbine: Single-stage compressor turbine, single-stage power turbine
Performance
- Maximum power output: 736 kW (987 shp) (maximum continuous)
See also edit
Related lists
References edit
- ^ a b c d "TM.333; a new generation turboshaft" (PDF). Flight International. 1 January 1983.
- ^ a b "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
External links edit
- Turbomeca TM 333