Rotor blade arrangement and gas turbine

摘要

A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).

主权项

1. A rotor blade arrangement which can be fastened on a blade carrier, the rotor blade arrangement comprising:
a blade aerofoil element; and a platform element, wherein the platform element is configured and arranged to form a part of a blade row continuous inner shroud; wherein the blade aerofoil element and the platform element are separate elements and are each configured and arranged to be separately fastened on the blade carrier; and wherein the blade aerofoil element and the platform element are configured and arranged to be mechanically decoupled during operation of the rotor blade arrangement; wherein the blade aerofoil element comprises:
an aerodynamically shaped blade aerofoil having a bottom;a shank which adjoins the blade aerofoil at the blade aerofoil bottom and is shrouded by the platform element, the shank having a bottom; anda blade root which adjoins the shank at the shank bottom, the blade root being configured and arranged to fasten the blade aerofoil element on the blade carrier; wherein the blade aerofoil element is formed in one piece and the platform element is formed in one piece; wherein the blade carrier includes an axial slot for fastening the blade aerofoil element on the blade carrier; a platform element fastener configured and arranged to fasten the platform element on the blade carrier separate from the blade aerofoil element, and the fastener being configured and arranged to engage in the blade carrier axial slot; wherein the blade aerofoil element comprises the blade root with a firtree profile, and the platform element fastener comprises legs configured and arranged to be hooked into the blade carrier slot above the blade root; a horizontal shoulder over which the platform element fits, is formed on the blade aerofoil; and seals configured and arranged to seal gaps between the blade aerofoil element and the platform element, the seals positioned between the horizontal shoulder of the blade aerofoil element and the platform element, wherein the seals transmit substantially no forces between the blade aerofoil element and the platform element.