| 摘要 |
<p>A gas turbine combustor includes a combustor liner (150) enclosing a combustion chamber; at least one fuel nozzle arranged to provide fuel to the combustion chamber; a flow sleeve (178) surrounding the combustor liner forming a passage (154) radially between the combustor liner and the flow sleeve for supplying air to the combustion chamber, the flow sleeve configured to permit air to flow substantially axially into the passage via a substantially annular flow sleeve inlet (156). A downstream end (176) of the flow sleeve is formed to include an annular manifold (180) provided with plural outlets (182) about a circumference of the downstream end of the flow sleeve and adapted to supply supplemental air from an external variable air source substantially radially into the passage to thereby maintain axial air flow boundary layer attachment at the flow sleeve inlet.</p> |
