| 摘要 |
<p>A gas turbine engine of the type having generally cylindrical casings (19,21) defining concentric bypass and turbine discharge passages (23,35) including a support structure (37) in the turbine discharge passage. The support structure (37) is cooled with low pressure compressor discharge air through a scoop (141) located in the bypass gas passage (23). The support structure (37) includes a plurality of radial fairings (67), each of which includes discharge openings (107) and, preferably, a discharge chute (75) which is approximately perpendicular to its respective fairing (67). The discharge openings (107) each communicate with the compressor discharge cool air flow in its respective fairing so as to provide a discharge flow (which from the chutes (75) is in the form of a stratified annulus) to cool downstream members which are aligned with them. The cooling air further reduces the temperature of the downstream gases so as to reduce the potential for flashback in the engine. The aerodynamic form and placement of the discharge chutes (75) provide enhancements to the operation of the diffuser, of which the support structure is a part.</p> |
