Rolls-Royce Clyde
{{short description|1940s British turboprop aircraft engine}}
{{Use dmy dates|date=January 2018}}
{{Use British English|date=January 2018}}
| {{Infobox aircraft begin
|name= RB.39 Clyde |image= Rolls-Royce Clyde RRHT Derby.jpg |caption= Rolls-Royce Clyde on display at the Rolls-Royce Heritage Trust, Derby }}{{Infobox aircraft engine |type= Turboprop |manufacturer= Rolls-Royce Limited |first run= 5 August 1945{{cite book|last=Kay|first=Anthony L.|title=Turbojet History and Development 1930-1960 vol.1|publisher=The Crowood Press|location=Marlborough|year=2007|edition=1st|pages=105–118|chapter=14|isbn=978-1-86126-912-6}} |major applications= |program cost = |unit cost = |developed from = |developed into = |variants with their own articles = }} |
The Rolls-Royce RB.39 Clyde was Rolls-Royce's first purpose-designed turboprop engine and the first turboprop engine to pass its civil and military type-tests.Flight 1954, p. 582.
As with subsequent Rolls-Royce gas turbines, it was named after a river, the River Clyde.
Design and development
The Clyde used a two-shaft design, with an axial compressor based on that of the Metrovick F.2{{Cite book
|title=Axial Compressor Development at Rolls-Royce Derby, 1946–1962
|first=A. |last=McKenzie
|id=Technical Series Nº11
|publisher=Rolls-Royce Heritage Trust
|isbn=978-1-872922-42-3
|year=2001
|pages=10, 23
}}"World Encyclopedia of Aero Engines – 5th edition" by Bill Gunston, Sutton Publishing, 2006, P.195 for the low-pressure section, and a single-sided centrifugal compressor scaled up from the Merlin 46 supercharger{{Cite journal|url=http://www.royalsocietypublishing.org/doi/pdf/10.1098/rsbm.2005.0013|doi = 10.1098/rsbm.2005.0013|title = Lionel Haworth. 4 August 1912 — 12 April 2000|year = 2005|last1 = Feilden|first1 = G. B. R.|journal = Biographical Memoirs of Fellows of the Royal Society|volume = 51|pages = 195–220|s2cid = 60786773}}
as the high-pressure stage, both mounted on the HP shaft and driven by a single stage HP turbine. A single stage power turbine drove the front mounted propeller reduction gearbox via the concentric LP shaft. A fairly novel feature of this compact gearbox was the power output to contra-rotating propellers."Not much of an Engineer" by Sir Stanley Hooker, Airlife Publishing Ltd, 1984, P.227
The Clyde was a long engine with the axial LP compressor in front of what was, in effect, a scaled-down Derwent engine. Accessories were grouped around the axial compressor which conveniently narrowed towards the rear. Cooling for turbines and turbine bearings came from a small impeller on the main shaft as well as air taken from the axial and centrifugal compressors. Testing of the development engines exceeded expectations with the engine soon being rated at 4,030 eshp.
During testing potentially destructive vibrations were found originating in the straight-cut spur gears in the reduction gearbox.
The engine was selected as the main engine of the Westland Wyvern TF Mk.2 strike aircraft. However, despite the promising performance of the test engines Ernest Hives felt that pure-jets such as the Avon were the future and the Clyde programme was terminated, forcing Westland to use the less than satisfactory Armstrong Siddeley Python on the production Wyverns. and so Rolls-Royce's first production turboprop would be the Dart.
Engines on display
A part sectioned example is on display at the Rolls-Royce Heritage Trust, (Derby).
Specifications (Clyde)
File:Rolls-Royce Clyde RRHT Derby (side view).jpg
{{jetspecs
|ref=Turbojet History and Development 1930-1960 vol.1.
|type=Two-Shaft Turboprop
|length={{convert|121.2|in|mm|abbr=on}}
|diameter={{convert|46.8|in|mm|abbr=on}}
|weight={{convert|2800|lb|kg|abbr=on}} (dry)
|compressor=LP - 9 stage axial, HP - Single centrifugal stage
|combustion=Eleven can-type combustion chambers
|turbine=HP - single stage axial, Power' - single stage axial
|fueltype=Kerosene (jet fuel grade)e
|oilsystem=Pressure spray scavenge system
|power=4,030 eshp (3,006 kW)
|thrust=
|compression=6:1
|aircon={{convert|41.5|lb/s|kg/s|abbr=on}}
|turbinetemp=
|fuelcon=
|specfuelcon=0.71 lb/hp/hr (0.432 kg/kW/hr)
|power/weight=1.439 eshp/lb (2.09 kW/kg)
|thrust/weight=
}}
See also
References
{{Commons category}}
=Notes=
{{reflist}}
=Bibliography=
{{refbegin}}
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}}
- {{cite book|last=Kay|first=Anthony L.|title=Turbojet History and Development 1930-1960 vol.1|publisher=The Crowood Press|location=Marlborough|year=2007|edition=1st|pages=105–118|chapter=14|isbn=978-1-86126-912-6}}
- King, H. F. [http://www.flightglobal.com/pdfarchive/view/1954/1954%20-%201286.html "The Two R's: A Commemorative History of Rolls-Royce Aero Engines. (article and images).]" Flight No. 2363, Volume 65, 7 May 1954.
{{refend}}
{{Rolls-Royce aeroengines}}