Patent ID: 8757965

Claim:
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 gas in the channel, the low pressure compressor section ( 8 ) comprising an alternating series of rotating rotor blades and stationary stator blades with the last blades in the series being rotor blades, and a compressor structure ( 14 ) arranged between the low pressure compressor section ( 8 ) and the high pressure compressor section ( 9 ), wherein the compressor structure ( 14 ) is 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, with the struts being spaced by a distance downstream from the last low-pressure-compressor rotor blades in the series with no intervening stator blades therebetween, wherein at least one of said struts is hollow for housing service components, and wherein the compressor structure ( 14 ) is designed for substantially turning a swirling gas flow from the last low-pressure-compressor rotor blades in the series by virtue of a plurality of said struts ( 15 , 16 , 21 , 24 , 25 ) having a cambered shape.