Turbomeca Turmo

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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 894.84 kW (1,200 hp) turboshaft powering the Sud-Aviation Frelon prototypes.
Turmo IIIC₂: Developed from the IIIC delivering 969.41 kW (1,300 hp) maximum output
Turmo IIIC₃: Maximum rating 1,118.55 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 913.48 kW (1,225 hp).
Turmo IIID₂: 995.51 kW (1,335 hp) at 22,460 free turbine rpm
Turmo IIID₃: 1,081.26 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 1,342.26 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

Turboprop

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
Power-to-weight ratio: 3.74 kW/kg (2.28 shp/lb)

References

↑ 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

Wikimedia Commons has media related to Turbomeca Turmo.

Turbomeca website

Turbomeca aero engines

Gas generators/Auxiliary power units

Turbojets

Turbofans

Turboprops/Turboshafts

Joint development

HAL/Turbomeca:	Ardiden/Shakti (Turboshaft)

MTU Turbomeca Rolls-Royce:	MTR390 (Turboshaft)

Rolls-Royce Turbomeca Limited:	Adour (Turbofan) RTM322 (Turboshaft)

Snecma/Turbomeca:	Larzac (Turbofan)

v t e People's Republic of China military aircraft engine designation system

Piston Engines	HS-5 HS-6 HS-7 HS-8

Turbojets	PF-1 WP-5 WP-6 WP-7 WP-8 WP-11 WP-13 WP-14

Turboprops/Turboshafts	WJ-5 WJ-6 WZ-6 WZ-5 WZ-8 WZ-9 WZ-16

Turbofans	WS-6 WS-8 WS-9 WS-10 WS-11 WS-13 WS-15

Abbreviations: HS - HuoSai - Piston Engines WJ - WoJiang - Turboprop WP - WoPen - Turbojet WS - WoShan - Turbofan WZ - WoZhou - Turboshaft

v t e Lists relating to aviation

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Records	Airspeed Altitude Distance Endurance Firsts Large Most-produced aircraft Most-produced rotorcraft

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