Turbomeca Turmo

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

The Turbomeca Turmo is a French turboshaft engine developed for helicopter use. A descendant of Turbomeca's pioneering Artouste design, later versions delivered around 1,200 kW (1,610 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 license 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 Peoples 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

Turboprop

• Breguet 940
• Breguet 941
• Breguet 941S

Specifications (Turmo IIIC₇)

Data from Flight International.^[1]

General characteristics

• Type: Two-shaft turboshaft
• Length: 182 cm (71.6 in)
• Diameter: 71.6 cm (28.2 in)
• Dry weight: 325 kg (716 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 shp)
• Overall pressure ratio: 5.9:1
• Air mass flow: 6.2 kg/s (13.7 lb/sec)
• Power-to-weight ratio: 3.74 kW/kg (2.28 shp/lb)

See also

Related lists

• List of aircraft engines

References

1. Flight International 7 January 1978, p. 69. Retrieved: 18 December 2012

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

External links

• Turbomeca website