Engineering:Turbomeca Turmo III
From HandWiki
| Turmo III | |
|---|---|
| |
| Turbomeca Turmo IIIB | |
| Type | Turboshaft/turboprop |
| Manufacturer | Turbomeca |
| Major applications | Aérospatiale Puma Aérospatiale Super Frelon |
| Developed into | Bristol Siddeley Nimbus |
The Turbomeca Turmo III is a French turboshaft engine developed for helicopter use. A descendant of Turbomeca's pioneering Artouste design, later versions delivered around 1,200 kW (1,600 shp). A turboprop version was developed for use with the Breguet 941 transport aircraft.
Current versions are built in partnership with Rolls-Royce, and the engine is produced under licence by the Chinese Changzhou Lan Xiang Machinery Works as the WZ-6 and Romanian Turbomecanica, Bucharest, as the Turmo IV-CA.
Variants
- Turmo IIIC
- A 890 kW (1,200 hp) turboshaft powering the Sud-Aviation Frelon prototypes.
- Turmo IIIC2
- Developed from the IIIC delivering 970 kW (1,300 hp) maximum output
- Turmo IIIC3
- Maximum rating 1,100 kW (1,500 hp) at 33,500 rpm for production Super Frelon helicopters
- Turmo IIIC4
- Turmo IIIC5
- Turmo IIIC6
- Turmo IIIC7
- Turmo IIID
- Turboprop for the proposed Breguet Br 942 STOL transport, maximum rating 913 kW (1,225 hp).
- Turmo IIID2
- 996 kW (1,335 hp) at 22,460 free turbine rpm
- Turmo IIID3
- 1,080 kW (1,450 hp) at 33,500 rpm
- Turmo IVB
- Turmo IVC
- Turmo IV-CA
- Licence production in Romania
- Turmo VI
- Turboprop engine with two axial stages, one centrifugal compressor stage and two free power turbine stages, rated at 1,300 kW (1,800 hp) at 32,000 rpm.
- WZ-6
- Licence production at the Changzhou Lan Xiang Machinery Works in the People's Republic of China.
Applications
- Turboshaft
- Aérospatiale Puma
- Aérospatiale Super Frelon
- Aérospatiale Super Puma
- Bölkow Bo 46
- IAR 330
- SNCASE SE.3200 Frelon
- Turbotrain
- SNCF Class T 2000
- N.300 Naviplane
- Turboprop
- Automobile
- Renault Étoile Filante
Specifications (Turmo IIIC7)
Data from Flight International.[1]
General characteristics
- Type: Two-shaft turboshaft
- Length: 182 cm (71.65 in)
- Diameter: 71.6 cm (28.19 in)
- Dry weight: 325 kg (717 lb)
Components
- Compressor: Single-stage axial, single-stage centrifugal
- Combustors: Annular, reverse-flow
- Turbine: Two-stage compressor turbine, two-stage power turbine
Performance
- Maximum power output: 1,217 kW (1,632 hp)
- Overall pressure ratio: 5.9:1
- Air mass flow: 6.2 kg/s (820 lb/min)
- Power-to-weight ratio: 3.74 kW/kg (2.27 hp/lb)
See also
Related lists
References
- ↑ "International turbine engine directory". Flight International 113 (3590): 69. 7 January 1978. http://www.flightglobal.com/pdfarchive/view/1978/1978%20-%200057.html. Retrieved 12 March 2019.
Further reading
- Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. pp. 163.
External links
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