| 摘要 |
<p>A gas turbine engine (10) comprises a compressor (14), a combustion chamber (15), an outer casing (20), an inner casing (22) and a cooling arrangement (24). The outer casing (20) surrounds the compressor (14) and the combustion chamber (15) and the combustion chamber (15) has turbine nozzle guide vanes (26). The compressor (14) has load carrying outlet guide vanes (28) connected to the outer casing (20) and the inner casing (22). The turbine nozzle guide vanes (26) connect the outer casing (20) and the inner casing (22). The cooling arrangement (24) comprises a cooling air duct (38) located between the compressor (14) and the combustion chamber (15). The compressor outlet guide vanes (28) carry at least one aerodynamic fairing (40). A support structure (42) supports the cooling air duct (38) from the inner casing (22) at two spaced positions and the support structure (42) forms a chamber (50) with the inner casing (22). The support structure (42) comprises at least one hollow duct (48) and each hollow duct (48) locates behind a respective one of the aerodynamic fairings (40).</p> |
