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Turbomeca Piméné
First run in 1948, the Turbomeca Piméné was a small French turbojet engine produced by Turbomeca in the early 1950s. A single-stage compressor, annular combustion with rotating fuel delivery ring and single-stage turbine, the Pimémé first flew in the Fouga Cyclone powered-sailplane on July 14, 1949.
The Pimene has a single-stage centrifugal compressor with a 3.8 : 1 compression ratio.
The combustion chamber is annular, with rotary fuel injection. The fuel ring, around the periphery of which are a number of vents, is attached to the shaft connecting compressor and turbine dises and revolver with it. Fuel is fed into the inside of the ring and is vented by centrifugal force, being vaporised in the process. Fuel delivery at low thrust settings regulated by by-pass valve.
The turbine is single-stage single-piece turbine with 31 blades preceded by stator with twenty air-cooled valve. The starter is Air Equipement 24 volt electric or compressed-air starter. One igniter plug on first model, two after. The mounting has three mounting pans, two on compressor casing and one on underside of combustion chamber.
First shown at the 1949 Paris Air Show this engine passed official type tests in 1950. A variant known as the Turbomeca Orédon drove an alternator and was used as an aircraft auxiliary power unit, this name being reused for a later helicopter turboshaft design.
Max. T.O. (static) 110 kg. (242 lb.) at 35,000 r.p.m.
Crursing (static) 80 kg. (176 lb.) at 33,000 r.p.m
Length 1,050 mm. (41.5 in.).
Diameter 400 mm. (16 in.)
Weight dry: 54 kg (118 lb.)
Turbine rpm: 35,000
Gas temperature before turbine: 700°C
Gas temperature after turbine: 600°C
Fuel Pump: Martin Moulet
Maximum pressure: 4 kg./cm.2 (57 lb./sq. in.)
Fuel: Kerosene (Jet A1
Fuel burn max. T.O. 1.05 kg./kg. s.t./hr. (1.22 lb./ lb. s.t./hr.).
EFW N-20
Fouga CM.8
Fouga CM.101R
Fouga CM.88 Gemeaux
Type: Turbojet
Length: 80 cm (31.5 in)
Diameter: 40 cm (15.75 in)
Dry weight: 54 kg (119 lb)
Compressor: Single stage axial plus single-stage centrifugal
Combustors: Single annular combustion chamber
Turbine: Single-stage
Maximum thrust: 1 kN (220 lbf) at 37,000 rpm
Specific fuel consumption: 1.05 lb/hr/lbf
Thrust-to-weight ratio: 1.85

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