Abstract: A sealing ring for sealing off a gap, surrounding a rotor shaft, between a rear and a front stator unit, includes an upper left-hand sealing part and a lower right-hand sealing part that is opposite the latter via the rotor shaft, and an upper right-hand sealing part and a lower left-hand sealing part that is opposite the latter via the rotor shaft. Each of the four sealing parts has a circumferentially extending sealing portion, a contact portion arranged at the first end, an angle portion arranged at the opposite end and an overlapping portion adjacent to the angle portion, wherein in each case two contact portions and two overlapping portions overlap respective adjacent sealing parts.

Abstract: A guide vane ring which is divided into an upper and into a lower guide vane ring half, with an inner ring which is split at least in two, has a substantially U-shaped cross section, and forms a radially outwardly open flow duct which extends in the circumferential direction and is delimited by way of an inner ring bottom wall and two inner ring side walls, and with a multiplicity of vane platforms which receive guide vanes, are arranged along the outer circumference of the inner ring, and have holding webs which in each case project radially inwards, are spaced apart from one another in the axial direction, and engage around the inner ring side walls from the outside, wherein wear elements are inserted into gaps which are present between holding webs and directly adjacently arranged inner ring side walls.

Abstract: A guide vane ring which is divided into an upper and into a lower guide vane ring half, with an inner ring which is split at least in two, has a substantially U-shaped cross section, and forms a radially outwardly open flow duct which extends in the circumferential direction and is delimited by way of an inner ring bottom wall and two inner ring side walls, and with a multiplicity of vane platforms which receive guide vanes, are arranged along the outer circumference of the inner ring, and have holding webs which in each case project radially inwards, are spaced apart from one another in the axial direction, and engage around the inner ring side walls from the outside, wherein wear elements are inserted into gaps which are present between holding webs and directly adjacently arranged inner ring side walls.

Abstract: A turbine blade having an internally cooled turbine blade airfoil in which a hollow space is divided by rib elements into at least one cooling duct carrying a coolant, wherein in at least one of the rib elements a separating tear initiating device for producing a separating tear is disposed, which extends at least partially in the longitudinal direction of the at least one rib element.

Abstract: A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.

Abstract: A rotor blade for a gas turbine, the rotor blade having an aerofoil with a pressure side and an intake side which transition into a platform to which an attachment region is connected, the region having a fir tree spring which has a plurality of lateral toothed extensions arranged on the pressure side and the intake side, which extensions extend in an azimuthal direction. In addition, the azimuthal extent of one lateral toothed extension is reduced in an axial region of the lateral toothed extension, in which region the pressure load during operation exceeds a predefined threshold.

Abstract: A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.

Abstract: A turbine blade having an internally cooled turbine blade airfoil in which a hollow space is divided by rib elements into at least one cooling duct carrying a coolant, wherein in at least one of the rib elements a separating tear initiating device for producing a separating tear is disposed, which extends at least partially in the longitudinal direction of the at least one rib element.

Abstract: A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.

Abstract: A turbine blade with an internally cooled turbine blade airfoil, in which a hollow space is divided by rib elements in at least one cooling channel carrying a coolant, wherein a recess of material, which is arranged next to at least one rib element on a turbine blade airfoil wall, is embodied such that tensions occurring within the turbine blade airfoil can be reduced in a region surrounding the at least one rib element.

Abstract: A gas turbine includes a turbine having a rotor blade row and a ring that is arranged around the rotor blade row and is made up of multiple ring segments. An insert element covers a recess of a ring segment body of the turbine. The ring segment body has a recess on a hot-gas side. The insert element has a concavely shaped front face and a rear face with a rear face profile, and the rear face profile corresponds to a negative shape of a profile of the recess. A mounting method includes an insert element fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.

Abstract: A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Abstract: A turbine rotor blade for a gas turbine, including a blade root and an adjoining aerodynamically curved airfoil which has a suction-side lateral wall and a pressure-side lateral wall is provided herein. These lateral walls extend in the chord direction from a common leading edge to a trailing edge and in a span direction having a total span from a blade root end to a blade tip end, a coolant duct for guiding a coolant being provided in the airfoil. In order to provide a sufficiently coolable turbine rotor blade of a comparatively small profile thickness, the airfoil, starting from its blade root end, is devoid of cooling ducts as of a span of 75% of the total span, preferably 60% of the total span.

Abstract: A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.

Abstract: A turbine blade is provided having a blade and a modular platform which follow one another along a longitudinal axis of the turbine blade. In order to provide a modular turbine blade that has an especially plain and simple design and that ensures an especially reliable, long-lasting, durable connection of the individual components among each other, the blade has an extension and the platform has an outer platform part and an at least two-part inner platform part which is radial in relation to the longitudinal axis and which lie laterally against the extension of the blade, and the outer platform part is designed as an endless platform frame that surrounds the outer edge of the inner platform part.

Abstract: A turbine blade is provided, having a fastening section, a platform, and a blade, which follow one another along a longitudinal axis of the turbine blade, wherein the platform, in radial relation to the longitudinal axis, has an inner platform part and an outer platform part, wherein the outer platform part is designed as a closed platform frame that encloses the outer edge of the inner platform part. An associated method for producing a turbine blade is also provided.