AXIAL TURBOMACHINE HAVING ASYMMETRICAL COMPRESSOR INLET GUIDE BAFFLE

摘要

An axial flow machine having an asymmetrical air inlet and, downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes is characterized in that at least some of the guide vanes of the inlet guide baffle have a vane profile and/or an angle of attack that deviate(s) from the remaining guide vanes. The inlet flow angle of the first compressor stage is hereby evened out circumferentially symmetrically. This is accomplished in that the different inlet angles resulting at various circumferential positions of the inlet guide baffle due to the asymmetry of the air inlet, are influenced by selective profiling and/or by selectively modifying the angle of incidence of individual guide vanes in such a way that a circumferentially symmetrical outflow angle from the inlet vane ring results. In this way, the circumferential distortions caused by the asymmetrical air inlet are minimized and, thus, circumferentially symmetrical inlet conditions are passed onto the first compressor stage, which results in an improved stability and an enhanced efficiency of the compressor.