摘要:
The invention relates to a rotor (2) of a thermal turbomachine, particularly of a gas turbine, having a number of individual rotor parts (6) that are held together by a tie rod (4) and combined into a unit, ensuring a reliable and safe operation, even at an increased installation length of the gas turbine. The natural frequency of the tie rod (4) is to be shifted toward higher frequencies in comparison to the rotational speed of the turbine. For this purpose the tie rod (4) is supported by the assembly of the surrounding rotor components consisting of the tie rod and the rotor disks. In combination with the two-part hollow shaft (11), the support wheel represents a further supporting rotor component.
摘要:
A turbomachine (101) having a rotor, wherein the rotor comprises a central holding element (124) and rotor elements (122) 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 (126) is arranged in a region of the rotor between the holding element (124) and the rotor element (122), wherein the contact element (126) comprises a temperature measurement device (134).
摘要:
The invention relates to a rotor (2) of a thermal turbomachine, particularly of a gas turbine, having a number of individual rotor parts (6) that are held together by a tie rod (4) and combined into a unit, ensuring a reliable and safe operation, even at an increased installation length of the gas turbine. The natural frequency of the tie rod (4) is to be shifted toward higher frequencies in comparison to the rotational speed of the turbine. For this purpose the tie rod (4) is supported by the assembly of the surrounding rotor components consisting of the tie rod and the rotor disks. In combination with the two-part hollow shaft (11), the support wheel represents a further supporting rotor component.
摘要:
A turbine blade rotor assembly (10) provides sealing for the rotor components and bi-direction axially locking of the blades (22) on the rotor (12) using a seal plate (36) on the aft exhaust side (18) without axial locking on the forward intake side (16) of the rotor and blade array. As a result, the blades (22) can be removed from the aft direction without moving the turbine casing cover.
摘要:
The invention relates to a rotor section (10) for a rotor of a gas turbine, to a rotor blade (18), and to a blocking element (46, 62). The rotor section (10) comprises a rotor disk (12) having rotor blades (18) that are inserted thereon in holding grooves (16) and that are secured against sliding along the holding grooves (16) by means of a sealing element (30) 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 (30), it is proposed that each sealing element (30) be secured by one blocking element (46, 62), which engages in a hole (58) arranged at the end face in the rotor blade root (20).