Abstract: An outlet guide vane for an axial compressor extending along a rotor axis, includes an airfoil extending in a span direction from a radially inner end at 0% height to a radially outer end at 0% height. The airfoil has a suction side and an opposite pressure side, both sides extending in a chord direction from a leading edge to a trailing edge, wherein for each profile of the airfoil a stagger angle between the chord and the rotor axis is defined. A more favorable air flow profile behind the outlet guide vane is achieved by a new shape of the outlet guide vane, wherein a stagger angle distribution in the span direction has a curved course having a minimum located between 40% and 60% in the span direction, a first maximum at 0% and a second maximum at 100% in the span direction.

Abstract: An outlet guide vane for an axial compressor extending along a rotor axis, includes an airfoil extending in a span direction from a radially inner end at 0% height to a radially outer end at 0% height. The airfoil has a suction side and an opposite pressure side, both sides extending in a chord direction from a leading edge to a trailing edge, wherein for each profile of the airfoil a stagger angle between the chord and the rotor axis is defined. A more favorable air flow profile behind the outlet guide vane is achieved by a new shape of the outlet guide vane, wherein a stagger angle distribution in the span direction has a curved course having a minimum located between 40% and 60% in the span direction, a first maximum at 0% and a second maximum at 100% in the span direction.

Abstract: An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.

Abstract: An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.