摘要:
A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.
摘要:
A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.
摘要:
A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element which is arranged on the end face. In order to disclose a reliable construction which can be designed in a straightforward and simple manner for the circumferential fixing of the sealing element, each sealing element is secured by means of a blocking element in each case which in this case engages in a hole which is arranged in the rotor blade root on the end face.
摘要:
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.
摘要:
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.
摘要:
A turbomachine having a rotor is provided, wherein the rotor comprises a central holding element and rotor elements which are arranged thereon, is intended to permit faster start-up without reducing the lifetime of the rotor, while permitting better predictions relating to the remaining lifetime of the rotor. To this end, a contact element is arranged in a region of the rotor between the holding element and the rotor element, wherein the contact element comprises a temperature measurement device.
摘要:
A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving a turbine casing.
摘要:
A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving the turbine casing cover.
摘要:
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.
摘要:
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.