| 摘要 |
<p>The invention concerns a gas turbine having an axis X and comprising, from upstream to downstream, a high-pressure compressor whereof the rotor includes a downstream cone (4), a diffuser (3) extended downstream on the side of the axis X by an inner casing (5) arranged radially outside said compressor chamber downstream cone, a combustion chamber arranged radially outside said diffuser inner casing, and a high-pressure turbine whereof the rotor is connected to the compressor downstream cone through a connecting shaft, the diffuser inner casing and the compressor downstream cone delimiting between them a cavity beneath the chamber located downstream of a discharge labyrinth (13) and wherein circulates, from upstream to downstream, a cooling air. The invention is characterized in that it further comprises a stator shroud (20) installed beneath the diffuser inner casing (5) downstream of the discharge labyrinth (13).</p> |
