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Rolls-Royce based the 10-stage HP compressor on an 8-stage run in the RB401 in the mid 1970's followed by a 9-stage run in the RJ.500. The V.2500 would use 10 stages, with the first 4 with variable stators, giving a pressure ratio of 20:1. [4] A single-stage booster was also part of the original configuration.
In 1999, the rotating compressor business was sold to Rolls-Royce and Cooper Energy Services merged with Nickles Industrial Manufacturing and purchased Elliot Turbocharger Group, Inc. [2] In 2001, Cooper Energy Services and Cooper Turbocompresor combined to form Cooper Compression, which was later named Compression Systems in 2005. [2]
Rolls Royce Goblin II numbered cutaway; the impeller of the centrifugal compressor is number 12. The very first jet engines used centrifugal compressors and they are still used on small turbojets and turbo shaft engines. The key component that makes a compressor centrifugal is the centrifugal impeller which contains a rotating set of blades.
The Clyde used a two-shaft design, with an axial compressor based on that of the Metrovick F.2 [4] [5] for the low-pressure section, and a single-sided centrifugal compressor scaled up from the Merlin 46 supercharger [6] as the high-pressure stage, both mounted on the HP shaft and driven by a single stage HP turbine. A single stage power ...
The Rolls-Royce RB.183 Tay is a medium-bypass turbofan engine, developed from the RB.183 Mk 555 Spey core and using a fan scaled directly from the Rolls-Royce RB.211-535E4 to produce versions with a bypass ratio of 3.1:1 or greater. The IP compressor and LP turbine were designed using technology from the RB.211 programme. [1]
A single-stage fan, driven by a three-stage LP turbine, supercharged the nine-stage HP compressor, which was driven by a two-stage air-cooled HP turbine. The combustor was annular and the exhaust separate jets. The HP compressor was based on a scale-up of the Rolls-Royce RB401 HP compressor, with a ninth stage added at the rear. Fan diameter ...
The Rolls-Royce RB.37 Derwent is a 1940s British centrifugal compressor turbojet engine, the second Rolls-Royce jet engine to enter production. It was an improved version of the Rolls-Royce Welland , which itself was a renamed version of Frank Whittle 's Power Jets W.2B.
Data from Rolls-Royce Heritage Trust General characteristics Type: Gas generator Length: Diameter: Dry weight: Components Compressor: 5-stage LP, 7-stage HP Combustors: 8 chamber, cannular Turbine: Single-stage LP and HP Performance Maximum power output: 28,500 shp (21.4 MW) Specific fuel consumption: 0.47 lb/hp/hr (0.287 kg/KWh) See also Related development Rolls-Royce Olympus References ^ a ...