Rolls-Royce Nimbus

 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 Westland Scout and Wasp helicopters 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.

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.

Technical Details:

Type: Turboshaft
Power: 968 shp (722 kW)
Compressor: Two-stage axial, single-stage centrifugal
Combustors: Annular
Turbine: Two-stage axial gas generator, single-stage power
Dimensions: length: 73.7 in (187.2 cm), dia: 38.7 in (98.3 cm)
Dry weight: 670 lb (304 kg)
Overall pressure ratio: 6.4:1
Turbine inlet temperature: 877C internal / EGT 550C max
Fuel consumption: 595 lbs/hr (270kg/hr)