Turbomeca Turmo III

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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.

Turmo III
Turbomeca Turmo IIIB.jpg
Turbomeca Turmo IIIB
Type Turboshaft/turboprop
Manufacturer Turbomeca
Major applications Aérospatiale Puma
Aérospatiale Super Frelon
Developed into Bristol Siddeley Nimbus

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.


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.
Licence production at the Changzhou Lan Xiang Machinery Works in the People's Republic of China.



Specifications (Turmo IIIC7)Edit

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)


  • Compressor: Single-stage axial, single-stage centrifugal
  • Combustors: Annular, reverse-flow
  • Turbine: Two-stage compressor turbine, two-stage power turbine


See alsoEdit

Related lists


  1. ^ "International turbine engine directory". Flight International. 113 (3590): 69. 7 January 1978. Retrieved 12 March 2019.

Further readingEdit

  • Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 163.

External linksEdit