| 摘要 |
A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a bleed system that is configured to receive bleed air from the compressor section. The bleed system includes a first inlet duct coupled to an upstream location of the compressor section and a second inlet duct coupled to a downstream location of the compressor section. The first inlet duct and the second inlet duct merge into a common duct. |
