Turbomeca Turmo
{{Short description|Family of turboshaft engines}}
| {{Infobox aircraft begin
|name= Turmo |image= File:Turbomeca Turmo IIIB.jpg |caption= Turbomeca Turmo IIIB }} {{Infobox aircraft engine |type= Turboshaft/turboprope |national origin= France |manufacturer= Turbomeca |first run= |major applications= Aérospatiale SA 321 Super Frelon |number built= |developed from= |developed into= Bristol Siddeley Nimbus |variants with their own articles= }} |
The Turbomeca Turmo is a family of French turboshaft engines manufactured for helicopter use. Developed from the earlier Turbomeca Artouste, later versions delivered up to {{cvt|1300|kW|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 {{cvt|270|hp|kW|order=flip}}.{{cite book |title=Jane's all the World's Aircraft 1957–58 |editor1-last=Bridgman |editor1-first=Leonard |year=1957 |publisher=Sampson Low, Marston & Company, Ltd |location=London}}
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.
Variants
Data from:-Jane's all the World's Aircraft 1957–58
;Turmo I: The initial version of the Turmo; max continuous gearbox output {{cvt|270|shp|order=flip}} at 3,000 rpm, at 33,750 rpm gas generator speed.
;Turmo II:Developed version of the Turmo I; max continuous gearbox output {{cvt|320|shp|order=flip}} at 34,000 rpm gas generator speed.
;Turmo III:With 2-stage free power-turbine, pressure ratio 5.7:1 ;Maximum shaft output {{cvt|750|shp|order=flip}}, max continuous {{cvt|600|shp|order=flip}} at 33,400 rpm
;Turmo IIIB:
;Turmo IIIC:A {{convert|1,200|hp|kW|abbr=on|disp=flip}} turboshaft powering the Sud-Aviation Frelon prototypes.
;Turmo IIIC2: Developed from the IIIC delivering {{convert|1,300|hp|kW|abbr=on|disp=flip}} maximum output
;Turmo IIIC3: Maximum rating {{convert|1,500|hp|kW|abbr=on|disp=flip}} 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 {{convert|1,225|hp|kW|abbr=on|disp=flip}}.
;Turmo IIID2:{{convert|1,335|hp|kW|abbr=on|disp=flip}} at 22,460 free turbine rpm
;Turmo IIID3:{{convert|1,450|hp|kW|abbr=on|disp=flip}} at 33,500 rpm
;Turmo IIIF:{{convert|860|kW|hp|abbr=on|disp=flip}} at 32,100 rpm for use on Turbotrain and TurbolinerGarde, M. R. (13 December 1974). [https://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1975/79771/V01BT02A058/2391526/v01bt02a058-75-gt-122.pdf Gas Turbine Train Development in France] (PDF). Paper Number 75-GT-122. The American Society of Mechanical Engineers. p. 3
;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 {{convert|1,800|hp|kW|abbr=on|disp=flip}} at 32,000 rpm.
;Turmo XII:{{convert|1200|kW|hp|abbr=on|disp=flip}} for use on Class T 2000 Turbotrain and TGV 001.Garde, M. R. (13 December 1974). [https://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1975/79771/V01BT02A058/2391526/v01bt02a058-75-gt-122.pdf Gas Turbine Train Development in France] (PDF). Paper Number 75-GT-122. The American Society of Mechanical Engineers. p. 7, 8
;WZ-6:Licence production at the Changzhou Lan Xiang Machinery Works in the People's Republic of China.
Applications
;Turboshaft
- Sud-Est SE.3140 Alouette II
- Aérospatiale SA 321 Super Frelon
- Aérospatiale SA 330 Puma
- Bölkow Bo 46
- IAR 330
- SNCASE SE.3200 Frelon
- N.300 Naviplane
;Turboprop
;Automobile
;Train
Specifications (Turmo IIIC<sub>7</sub>)
{{jetspecs
|type=Two-shaft turboshaft
|length= {{cvt|182|cm|in|2}}
|diameter={{cvt|71.6|cm|in|2}}
|weight= {{cvt|325|kg}}
|compressor=Single-stage axial, single-stage centrifugal
|combustion=Annular, reverse-flow
|turbine=Two-stage compressor turbine, two-stage power turbine
|fueltype=
|oilsystem=
|power= {{cvt|1217|kW}}
|thrust=
|compression=5.9:1
|aircon={{cvt|6.2|kg/s}}
|turbinetemp=
|fuelcon=
|specfuelcon=
|power/weight= {{cvt|3.74|kW/kg}}
|thrust/weight=
}}
See also
{{aircontent
|see also=
|related=
|lists=
|similar engines=
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References
{{reflist}}
Further reading
- {{cite book |last= Gunston |first= Bill |title=World Encyclopedia of Aero Engines |year=1986 |publisher=Patrick Stephens |location= Wellingborough |pages=163 }}
External links
{{Commons category}}
- [https://web.archive.org/web/20061122214952/http://www.turbomeca.com/public/turbomeca_v2/html/en/produits/sous_famille_home.php?sfid=512&mid=615 Turbomeca website]
{{Turbomeca aeroengines}}
{{People's Republic of China military aeroengines}}
Category:Turbomeca aircraft engines