Rolls-Royce Soar

The Rolls- Royce RB.82 Soar (originally Soar RSr.2, later Rolls- Royce RB.93 ) was a turbojet engine in the axial structure of the British manufacturer Rolls- Royce. It represented a milestone in the development of drives with high thrust -to-weight ratio, and went on to develop dedicated lift engines for VTOL aircraft.

History

The engine was designed in 1949 by Alan Arnold Griffith, the chief developer of Rolls- Royce. The housing forming a welded sheet metal tube in which a single-stage axial compressor, an annular combustor and a turbine stage have been installed, wherein the turbine compressor and seated on a common shaft. While the inlet cone, which also contributed to the generator, was held by four struts, it was the outlet cone seven. The engine was developed under strict secrecy, because it should serve as a drive for the Red Rapier missile. In June 1952, reached a service life of only 2-3 hours at a thrust of 6.1 kN for test runs. Later, the service life to 10 h and the thrust of 8.27 kN was increased. Difficulties were the short combustion chamber, which was difficult to ignite and the lower power range unstable worked. To test received a Gloster Meteor F.8 to the RAF serial number WA982 two of these engines on the wingtips. However, the problems could not be eliminated.

As the Red Rapier Project 1953 has been set, it resulted in August 1954 the test vehicle in front at the Farnborough Air Show. In 1955 Canadian Aviation Electronics out a drone called the Canadian Aviation Electronics P-1 or Caeta, which was powered by a Rolls- Royce Soar. After the development of more powerful engines such as the Rolls- Royce RB.108, put Rolls -Royce to 1957, the development of a RB.82 Soar. Westinghouse still got a few engines under the name RB.93 that have been adapted to American standards. Later the company also got a manufacturing license. The engine was now under the U.S. designation Westinghouse J81 and was incorporated into the supersonic missile Northrop AQM - 35, while the proposed use in the Northrop GAM -67 was abandoned. For the Aerfer Ariete it was intended as a thruster, but there was no mass production.

Specifications

  • Weight: 121 kg
  • Diameter: 401 mm
  • Length: 1497 mm ( without inlet and generator panel)
  • Thrust: 8.27 kN
  • Compression ratio: 4.5:1
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