Abstract: The present disclosure describes an intervertebral disk replacement system. The system can include a tissue-engineered intervertebral disc that is combined with a bioresorbable stabilization system for structural guidance. The system can prevent or reduce intervertebral disk implant displacement and can increase the stiffness when compared to the implantation of the intervertebral disk implant without the stabilization system.

Abstract: The present disclosure describes an intervertebral disk replacement system. The system can include a tissue-engineered intervertebral disc that is combined with a bioresorbable stabilization system for structural guidance. The system can prevent or reduce intervertebral disk implant displacement and can increase the stiffness when compared to the implantation of the intervertebral disk implant without the stabilization system.

Abstract: The present disclosure describes an intervertebral disk replacement system. The system can include a tissue-engineered intervertebral disc that is combined with a bioresorbable stabilization system for structural guidance. The system can prevent or reduce intervertebral disk implant displacement and can increase the stiffness when compared to the implantation of the intervertebral disk implant without the stabilization system.

Abstract: The present disclosure describes an intervertebral disk replacement system. The system can include a tissue-engineered intervertebral disc that is combined with a bioresorbable stabilization system for structural guidance. The system can prevent or reduce intervertebral disk implant displacement and can increase the stiffness when compared to the implantation of the intervertebral disk implant without the stabilization system.

Abstract: A turbine blade, particularly a guide blade for a gas turbine, is provided. The turbine blade includes a blade leg, a platform area and a hollow blade for receiving a metal plate-type impact cooling insert which consists of at least two sections which overlap in an overlap area. The two sections have a wave-shaped cross-section in the overlap area in order to seal said overlap area.

Abstract: A cooled component of a fluid-flow machine, through which a hot working medium flows, in particular a turbine blade of a gas turbine, in whose outer wall, to which the working medium can be applied, a cooling passage is provided, through which a cooling fluid can flow along its longitudinal axis.

Abstract: The invention relates to a turbomachine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbomachine. The aim of said invention is to develop a device and a method for the turbomachine making it possible to reduce the size of a radial split of the turbomachine in order to obtain greater degree of efficiency. The inventive turbomachine comprises a rotor rotationally mounted in the case of the turbomachine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbomachine rotor by heating fluid flowing therethrough are also disclosed.

Abstract: The invention relates to a turbine blade, particularly a guide blade for a gas turbine, respectively comprising a blade leg, a platform area and a hollow blade for receiving a metal plate-type impact cooling insert which consists of at least two sections which overlap in an overlap area. The aim of the invention is to provide a turbine blade wherein les coolant is required. The two sections thus have a wave-shaped cross-section in the overlap area in order to seal said overlap area.

Abstract: A cooled component of a fluid-flow machine, through which a hot working medium flows, in particular a turbine blade of a gas turbine, in whose outer wall, to which the working medium can be applied, a cooling passage is provided, through which a cooling fluid can flow along its longitudinal axis.

Abstract: In a device for rough turning and shaft turning of a workpiece, a cutting insert is provided with a main cutting edge followed by an auxiliary cutting edge. The main cutting edge is divided into a first main cutting edge functioning as a rough cutter followed by a second main cutting edge performing rough smoothing and then by the auxiliary cutting edge which provides the final smoothing. The first main cutting edge is set at a greater angle to the axis of the workpiece than the second main cutting edge which, in turn, is set at a greater angle to the axis of the workpiece than the auxiliary cutting edge.