| 摘要 |
<p>A diffuser (20) comprises a downstream portion (25) which is inclined relative to axis (A) of turbomachine towards a combustion chamber (10) such that the mean axis of a gas flow path passes through chamber end wall. The curvilinear abscissa distance along flow line between middle portion of flow path at trailing edges of flow-straightening vanes (26), and center (C) of injection orifices (44) is greater or equal to three times the height of flow path and the number of flow-straightening vanes is four times greater than the number of injection systems.</p> |
