Bristol Siddeley Nimbus
Nimbus Mark 103
The Bristol Siddeley Nimbus, later known as the Rolls-Royce Nimbus, was a British turboshaft engine developed under license by Blackburn Aircraft Ltd. from the Turbomeca Turmo in the late 1950s. First run in July 1958, it was used on the Westland Scout and Westland Wasp helicopters.
The Nimbus is a turboshaft engine comprising a gas generator section, which consists of a three-stage compressor, (two axial stages and one centrifugal stage), driven by a two-stage turbine in conjunction with an annular combustion chamber, and a power output section consisting of a single-stage free turbine driving an output shaft via a two-stage reduction gearbox.
In the Scout and Wasp the main rotor drive is taken from the front of the gearbox and is transmitted beneath the gas generator via a flexible coupling, while the drive for the tail rotor is taken from the rear of the gearbox.
The fuel system is designed to control and govern the engine under all operating conditions and to provide safeguards against malfunctions, the pilot selecting rotor speed and the governing element automatically maintaining the rotor speed within close limits under varying conditions of load.
The lubrication system is self-contained, the oil tank being integral with the air intake casing.
Engine and helicopter accessories are mounted on a gearbox located on the air intake casing.
The Nimbus engines were produced in two main variants, the Mark 103/503 and the Mark 105/502. The Mark 103/503 is generally similar to the Mark 105/502 except that the former has a double-caliper disc brake incorporated in the output drive shaft to provide adequate braking of the helicopter's rotor in the high winds encountered over the deck of a fast moving ship, whereas the 105/502 has a single caliper unit.
Nimbus 502 (Mk.105)
Nimbus 503: (Mk.103)
Saunders-Roe SR.N2, Hovercraft
Length: 73.7 in (187.2 cm)
Diameter: 38.7 in (98.3 cm) across exhaust ducts
Dry weight: 670 lb (304 kg)
Compressor: Two-stage axial, single-stage centrifugal
Turbine: Two-stage axial gas generator, single-stage power
Fuel type: NATO F-30,34,40,42,44 Diesel, Gasoline(100 hrs)
Oil system: Dual scavenge, NATO O-149
Maximum power output: 968 shp (722 kW)
Overall pressure ratio: 6.4:1
Turbine inlet temperature: 877c internal / EGT 550c max
Fuel consumption: 595 lbs/hr (270kg/hr)
Specific fuel consumption: 0.681
Power-to-weight ratio: 1.44 shp/lb (2.37 kW/kg)