FIELD: engines and pumps.
SUBSTANCE: invention relates to gas turbine compressor device comprising a gas duct, low-pressure and high-pressure compressor sections intended for compressing gas in aforesaid duct and the compressor housing element arranged between aforesaid compressor sections to allow gas flow to pass via the gas duct and including a set of radial posts designed to transfer operating load, one of the said posts being made hollow to accommodate auxiliary elements therein. The compressor housing element is arranged downstream of the last low-pressure compressor section rotor and allows a notable change in direction of swirled gas flow from the said rotor with the help of curvilinear-shape posts.
EFFECT: compressor device that allows notably change direction of swirled gas flow from rotor by curvilinear-shape posts.
25 cl, 5 dwg
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