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Rolls-Royce Welland
The Rolls-Royce RB.23 Welland was Britain's first production jet engine.〔Janes 1989, p.268.〕 It entered production in 1943 for use on the Gloster Meteor. The name Welland is taken from the River Welland, in keeping with Rolls' naming of jet engines based on the smooth flow of air not unlike water in a river.
The engine was originally developed Frank Whittle's team at Power Jets and known as the W.2, Whittle's second design and the first intended for eventual production. Power Jets was working with Rover who referred to it as the W.2B/23. The relationship between the companies was strained due to Rover's inability to deliver working parts, and broke when Whittle learned that a team of Rover engineers had designed their own version, the W.2B/26. Fed up with Whittle, Rover handed the project to Rolls-Royce, where Stanley Hooker joined the team from Rolls' supercharger division. Hooker's experience in turbocompressor design, along with improved metals and combustion systems, put the engine back on track and it soon entered production.
The Welland was used only for a short time. Hooker continued development of the W.2B/26, which featured a greatly simplified layout. This soon entered production as the Rolls-Royce Derwent at improved power settings, and Welland-equipped Meteors were either reengined or retired.
==Design and development==
The W.2 was basically a larger version of Whittle's original flying design, the Whittle Supercharger Type W.1, or simply W.1, which flew in 1941 in the Gloster E. 28/39 experimental testbed aircraft. The engines used a single double-sided centrifugal compressor, or ''impeller'', with the compressed air being taken off at several ports around the extreme outer edge of the compressor disk. They both used Whittle's "reverse flow" design, in which the flame cans (combustion chambers) were placed around the turbine to produce a shorter engine. This required the heated air to flow forward before reversing its direction to pass through the single-stage axial-flow turbine. For the W.2, the impeller was in diameter and there were ten flame cans. Air was bled from the compressor and fed into the inner portion of the turbine for cooling. The entire engine weighed about .
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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