Abstract: An axial compressor for compressing a flow medium is provided and includes compressor stator blades, which fastened on a stator blade carrier, and compressor rotor blades, which are fastened on a compressor disk of a compressor shaft, wherein two consecutive compressor disks enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space. A cooling medium feed duct leads through a stator blade carrier and a compressor stator blade, and is arranged upstream of the last compressor disk, which cooling medium feed duct, at the tip end of the compressor stator blade facing the compressor shaft, via a discharge opening arranged there, opens into the hollow space, wherein this hollow space, via a cooling medium transfer passage which is led through the subsequent compressor disks, is connected to the rear hollow space.

Abstract: A gas turbine including a plurality of hook elements disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and including a stator blade support, is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the hook elements or the stator blade support has a substantially elliptical cross-sectional contour.

Abstract: An axial turbomachine including a rotor-blade cascade is provided. The turbomachine includes a casing in which the cascade is installed and a guide-blade carrier which encloses the cascade and is integrated into the inner side of the housing. The guide-blade carrier is arranged immediately adjacently to the blade tips faulting a radial gap, wherein the guide-blade carrier is mounted in the housing, such that it may be displaced parallel to the axis of the axial turbomachine, and includes an adjusting ring which is supported on contact surfaces on the housing and guide-blade carrier and may be rotated about the axis, wherein the contact surfaces of the adjusting ring and of the housing and/or of the guide-blade carrier are set with respect to a plane perpendicular to the axis, so that, when the adjusting ring is rotated about the axis, the guide-blade carrier is displaced axially by the adjusting ring.

Abstract: A heat-shield element (14), for lining a combustion-chamber wall (13), the chamber wall has a first wall (17) with a hot side (18) which can be loaded with a hot medium, a cold side (19) which lies opposite the hot side (18), and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) of the first wall (17) to a first height (25) beyond the cold side (19), the circumferential edge (24) extends on a fourth narrow side (23) to a second shorter height (26), substantially at the second height (26), a second wall (27) lies opposite the cold side (19) and extends over the width of the fourth narrow side (23) from the fourth narrow side (23) and over a part of the length of the narrow sides (20, 22), which adjoin the fourth narrow side; (23), the second wall (27) has an edge (29) at the end (28) thereof which faces away from the fourth narrow side (23), which edge (29) extends to the first height (25). Furthermore, a combustion chamber and a gas turbine are disclosed.

Abstract: An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air is guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Abstract: A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Abstract: A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.

Abstract: A blade for a turbine or a compressor, at least partially made of fiber-reinforced plastic, in particular carbon fiber reinforced plastic, being particularly durable under operating conditions is provided. The blade includes a blade body and a blade root. The blade body is substantially made of a folded fabric web made of fiber reinforced plastic, wherein a retaining loop is formed in the area of the fold, and wherein a blade surface is formed in the area of the fold, and wherein a blade surface is formed from the overlapping web ends. The blade root includes a longitudinal beam and at least two holders for anchoring the blade in a corresponding groove of a rotor, the holders being preferably each fixedly connected to the beam at both ends. The blade body is suspended on the beam by means of the retaining loop.

Abstract: An axial compressor for compressing a flow medium is provided and includes compressor stator blades, which fastened on a stator blade carrier, and compressor rotor blades, which are fastened on a compressor disk of a compressor shaft, wherein two consecutive compressor disks enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space. A cooling medium feed duct leads through a stator blade carrier and a compressor stator blade, and is arranged upstream of the last compressor disk, which cooling medium feed duct, at the tip end of the compressor stator blade facing the compressor shaft, via a discharge opening arranged there, opens into the hollow space, wherein this hollow space, via a cooling medium transfer passage which is led through the subsequent compressor disks, is connected to the rear hollow space.

Abstract: An axial turbomachine including a rotor-blade cascade is provided. The turbomachine includes a casing in which the cascade is installed and a guide-blade carrier which encloses the cascade and is integrated into the inner side of the housing. The guide-blade carrier is arranged immediately adjacently to the blade tips faulting a radial gap, wherein the guide-blade carrier is mounted in the housing, such that it may be displaced parallel to the axis of the axial turbomachine, and includes an adjusting ring which is supported on contact surfaces on the housing and guide-blade carrier and may be rotated about the axis, wherein the contact surfaces of the adjusting ring and of the housing and/or of the guide-blade carrier are set with respect to a plane perpendicular to the axis, so that, when the adjusting ring is rotated about the axis, the guide-blade carrier is displaced axially by the adjusting ring.

Abstract: An axial turbo-compressor for a gas turbine having a stator vane assembly that is formed by stator vanes having vane tips exposed on the hub side and a stationary shaft cover on the hub side and delimits the flow channel of the axial compressor is provided. A radial gap is designed between the shaft cover and the van tips that is minimally sized such that the axial turbo-compressor may still be assembled, and there is a plurality of recesses in the shaft cover, wherein one of the recesses is allocated to each vane tip that is arranged directly neighboring the vane tip allocated thereto and is sized such that during operation of the axial turbo compressor every vane tip may be plunged into the recess allocated thereto without one of the vane tips significantly contacting the shaft cover.

Abstract: A guide blade arrangement for an axial turbo-machine is provided. The guide blade arrangement includes at least one annular guide blade carrier and an inner ring arranged concentrically with respect to the guide blade carrier, between which guide blade carrier and inner ring a number of guide blades are arranged in a radial configuration. To obtain a low-wear and particularly durable fastening of the guide blade, which is supported by the guide blade carrier, to the inner ring, it is proposed that the guide blades are fastened resiliently to the inner ring. Here, the fastening is provided by means of a spring element. By means of the spring element, it is possible to ensure a uniform contact pressure of the guide blade head against the inner ring or if appropriate against a further spring element, such that occurring stresses and wear can be reduced.

Abstract: A gas turbine including a plurality of hook elements disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and including a stator blade support, is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the hook elements or the stator blade support has a substantially elliptical cross-sectional contour.

Abstract: An axial compressor for a gas turbine having passive radial gap control is provided. The axial compressor includes a guide vane support on which guide vanes are fastened so as to be arranged in a ring, wherein the vane tips of the guide vanes lie opposite a wall section. Thermal insulation is attached to the wall section in the section lying opposite the vane tips in order to equalize the expansion behavior of the guide vane support and the wall section, which by themselves react thermally in different manners, wherein the terminal insulation is matched in the heat input delay effect thereof to the wall section and to the guide vane support in such a way that the thermal expansion behavior of the guide vane support and the wall section is at least equalized over time during transient operation of the axial compressor.

Abstract: A turbine guide vane support for an axial-flow gas turbine is provided. The support includes a tubular wall having an inflow-side end and an outflow-side end for a hot gas flowing in the interior of the turbine guide vane support in a flow path of the gas turbine. Cooling channels for a coolant are provided in the wall. The cooling channels extend from a coolant inlet to a coolant outlet, respectively. At least one of the cooling inlets and one of the cooling outlets, respectively, is disposed at the outflow-side end of the turbine guide vane support, wherein the cooling channel associated with the respective inlet and outlet extends up to the inflow-side end of the turbine guide vane support and transitions to a redirecting area from which the respective cooling channel further extends to the outflow-side end.

Abstract: A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.