| 摘要 |
<p>A gas turbine combustor comprises a combustion chamber (3,4) mounted within an air supply manifold (1), the combustion chamber preferably having a fixed downstream portion (4) and a telescopically-movable upstream portion (3), a burner head (2) provided with a fuel injector means, a primary air inlet from the manifold into the combustion chamber defined between the burner head (2) and an upstream end of the telescopically-movable upstream portion (3), movement of the upstream portion of the combustion chamber towards the burner head serving to restrict the primary air inlet whilst opening a secondary air inlet from the manifold into the combustion chamber downstream of the burner head, and movement of the upstream portion of the combustion chamber away from the burner head serving to open the primary air inlet whilst restricting the secondary air inlet. <IMAGE></p> |
