Turmo
Turbomeca Turmo IIIB
Type Turboshaft/turboprope
National origin France
Manufacturer Turbomeca
Major applications Aérospatiale SA 321 Super Frelon
Aérospatiale SA 330 Puma
Bréguet 941
Developed into Bristol Siddeley Nimbus

The Turbomeca Turmo is a family of French turboshaft engines manufacturered for helicopter use. Developed from the earlier Turbomeca Artouste, later versions delivered up to 1,300 kW (1,700 shp). A turboprop version was developed for use with the Bréguet 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.

Design and development

The Turmo was initially developed with a single-stage centrifugal compressor, annular combustion chamber and single stage turbine. Power output was from a single-stage free power turbine and was initially 200 kW (270 hp).[1]

During early post-war helicopter development, the use of cold and hot rotor tip-jets was widely investigated. To provide large mass-flow air for efficient operation of the tip-jets, Turbomeca developed a gas turbine driven gas producer, powered by the free power-turbine of the Turmo to deliver the required gas flow.[1]

Variants

Data from:-Jane's all the World's Aircraft 1957–58[1]

Turmo I
The initial version of the Turmo; max continuous gearbox output 200 kW (270 shp) at 3,000 rpm, at 33,750 rpm gas generator speed.
Turmo II
Developed version of the Turmo I; max continuous gearbox output 240 kW (320 shp) at 34,000 rpm gas generator speed.
Turmo III
With 2-stage free power-turbine, pressure ratio 5.7:1 ;Maximum shaft output 560 kW (750 shp), max continuous 450 kW (600 shp) at 33,400 rpm
Turmo IIIB
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
Military variant.
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
Military Variant
Turmo IVC
Civil Variant
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
Turboprop
Automobile

Specifications (Turmo IIIC7)

Data from Flight International.[2]

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

See also

Related development

Related lists

References

  1. 1 2 3 4 Bridgman, Leonard, ed. (1957). Jane's all the World's Aircraft 1957–58. London: Sampson Low, Marston & Company, Ltd.
  2. ↑ "International turbine engine directory". Flight International. 113 (3590): 69. 7 January 1978. Retrieved 12 March 2019.

Further reading

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