| 摘要 |
<p>A combustor (10) for a gas-or liquid-fuelled turbine having a compressor to supply air to the combustor for combustion and cooling, comprises a radially inner member (20) which defines a combustion chamber (12) and a radially outer member (30), a passage (40) for said air being defined between the inner member and the outer member so as to extend alongside the combustion chamber over at least part of the length thereof and a fuel/air mixer (14) being provided at the upstream end of the combustion chamber, the cross-sectional area of the passage between the two members increasing over at least part of the length of the passage in a direction from the downstream end to the upstream end of the combustion chamber, the passage having an inlet adjacent to the downstream end of the combustion chamber whereby air from the compressor enters the passage at the inlet, and flows in a direction towards the mixer. <IMAGE></p> |
