| 摘要 |
<p>A gas turbine engine (10). The engine (10) comprises a first compressor (16, 18) coupled to a first turbine by a first shaft (38), the first turbine having first and second turbine stages (22, 26). A first combustor (20) is provided downstream of the first compressor (16, 18) and upstream of the first stage (22) of the first turbine. A second combustor (24) is provided downstream of the first stage (24) of the first turbine, and upstream of the second stage (26) of the first turbine. A further turbine (28) is provided downstream of the first turbine, and is coupled to a further compressor (14) by a further shaft (40).</p> |
