| 摘要 |
The invention relates to a gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) being designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15, 16, 21, 24, 25) for transmission of load, wherein at least one of said struts (15, 16, 21, 24, 25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from said rotor (10) by a plurality of said struts (15, 16, 21, 24, 25) having a cambered shape. |
