Abstract: A blade for a gas turbine has a leading edge and a trailing edge, which are connected by a pressure side and an intake side. In at least one segment of a stacking axis, the blade has a cross section with a profile with a common profile tangent at a leading edge region and a trailing edge region, a leading edge tangent at the leading edge, which is perpendicular to the common profile tangent, a trailing edge tangent at the trailing edge, which is perpendicular to the common profile tangent, and a camber line, which extends, at an equal distance from the pressure side and the intake side, from a center point of a leading edge circle, up to a center point of a trailing edge circle.

Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.

Abstract: The present invention relates to a blade (1) for a gas turbine, having a leading edge and a trailing edge, which are connected by a pressure side and an intake side, wherein, in at least one segment of a stacking axis, the blade has a cross section with a profile with a common profile tangent (P) at a leading edge region and a trailing edge region, a leading edge tangent (V) at the leading edge, which is perpendicular to the common profile tangent, a trailing edge tangent (H) at the trailing edge, which is perpendicular to the common profile tangent, and a camber line (S), which extends, at an equal distance from the pressure side and the intake side, from a center point (MV) of a leading edge circle (KV), up to a center point (MH) of a trailing edge circle.

Abstract: A transition channel for a turbine unit with at least two components is configured as a flow channel from one component of a first pressure to a component of a second pressure. The transition channel has support ribs, extending between envelope surfaces of the transition channel and having a profile that is configured for the deflecting of a flow from an inlet cross section to an outlet cross section of the transition channel. Flow splitter blades are arranged between the support ribs, having a smaller relative profile thickness than the support ribs and/or a shorter axial design depth or profile chord length than the support ribs. Thanks to the integration of the slim and/or short flow splitter blades (tandem blades), it is possible to largely dissipate parasite secondary flows.