Drive device for pivoting adjustable blades of a turbomachine
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[0033]FIG. 1 shows in a longitudinal partial section a turbomachine which is designed as a stationary gas turbine 1. The gas turbine 1 is intended for power generation. Inside, it has a rotor 3 which is rotatably mounted around a rotational axis 2 and which is also referred to as a turbine rotor assembly. In series, along the rotor 3, are an intake duct 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of burners 7 which are arranged rotationally symmetrically to each other, a turbine unit 8 and an exhaust duct 9. The annular combustion chamber 6 forms a combustion space 17 which communicates with an annular hot gas passage 18. Four turbine stages 10, connected in series, form the turbine unit 8 there. Each turbine stage 10 is formed from two blade rings. A row 14 formed from rotor blades 15 follows a blade row 13 in each case in the hot gas passage 18, as seen in the flow direction of a hot gas 11 which is produced in the annular combustion chamber 6. The ...
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