| 摘要 |
A gas turbine engine having two compressor spools including in each spool centrifugal compressors [14, 16] driven by respective turbine stages. Each of the compressors are in series, the exhaust of the first compressor [14] being the input of the second compressor [16]. A third turbine stage [76, 74] is provided which is directly connected to a shaft [S3] adapted for mechanical work. The spools including the centrifugal compressors [14, 16] are mounted on independent concentric shafts [S1, S2].
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