Rolls-Royce RB162

The Rolls-Royce RB.162 was a simply constructed and lightweight British turbojet engine produced by Rolls-Royce Limited. Developed in the early 1960s, the RB.162 was designed to meet an anticipated need for a lift engine to power VTOL aircraft with the emphasis on simplicity, durability and lightweight construction. Development costs were shared by Britain, France and Germany after signing a joint memorandum of agreement. The engine featured fibre glass compressor casings and plastic compressor blades to save weight which also had the effect of reducing production costs. The engine has no oil system, a metered dose of oil instead being injected into the two main bearings by the compressed air used to turn the compressor at startup. Although the RB.162 was a successful design the expected large VTOL aircraft market did not materialise and the engine was only produced in limited numbers.
 
In 1966 British European Airways (BEA) had a requirement for an extended range aircraft to serve Mediterranean destinations. After a plan to operate a mixed fleet of Boeing 727 and 737 aircraft was not approved by the British Government Hawker Siddeley offered BEA a stretched and improved performance version of the Trident that they were already operating. This variant, the Trident 3B, used, in addition to its three Rolls-Royce Spey turbofan engines, a centrally mounted RB.162-86 which was used for takeoff and climb in the hot prevailing conditions of the Mediterranean area. The 'boost' engine was shut down for cruising flight. Some conversion was needed for the change from vertical to horizontal installation. With the RB.162 fitted the Trident 3B had a 15% increase in thrust over the earlier variants for an engine weight penalty of only 5%.

First run in January 1962, only 86 were built.

A design study for a turbofan version of the RB.162 was designated RB.175. Another projected derivative, the RB.181 was to be a scaled down version of the RB.162 producing approximately 2,000 lbs of thrust. Seven of these lift engines were to power the unbuilt Lockheed/Short Brothers CL-704 VTOL variant of the F-104 Starfighter.   

Applications:
Dassault Mirage IIIV
Dornier Do 31
Hawker Siddeley Trident 3B
VFW VAK 191B

RB.162-86
Type: Single spool turbojet
Length: 51.6 in (1311 mm)
Diameter: 25.0 in (635 mm)
Dry weight: 280 lbs (127 kg)
Compressor: 6-stage axial flow
Combustors: Annular
Turbine: Single-stage axial flow
Maximum thrust: 5,250 lb (23 kN)
Thrust-to-weight ratio: 18.75:1