Abstract: There is provided a blade tip for a rotary blade. The blade tip is formed of a metal foam and comprises at least one vortex generator. The vortex generator may comprise at least one passageway and/or cavity in the blade tip. In use, a vortex is created between the blade tip and a fan casing adjacent the blade tip.

Abstract: There is provided a blade tip for a rotary blade. The blade tip is formed of a metal foam and comprises at least one vortex generator. The vortex generator may comprise at least one passageway and/or cavity in the blade tip. In use, a vortex is created between the blade tip and a fan casing adjacent the blade tip.

Abstract: 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) 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, wherein at least one of the struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream of a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from the rotor (10) by a plurality of the struts (15,16,21,24,25) having a cambered shape.

Abstract: A vane assembly configured for turning a flow in a gas turbine engine includes a stationary main guide vane and an additional guide vane, wherein a leading edge of the additional guide vane is positioned upstream of a leading edge of the main guide vane and wherein the additional guide vane extends a distance along the main guide vane towards a trailing edge of the main guide vane forming a passageway between the additional guide vane and the main guide vane.

Abstract: 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.