| 摘要 |
A turbine blade, in the blade root ( 2 ) of which a curved and converging micro-turbine nozzle is provided, includes a passage duct ( 6 ) with large diameter originating at a cooling-air chamber ( 3 ) in the blade root, with a separately prefabricated micro-turbine nozzle element ( 7 ) with minimized flow cross-section, that is variably adaptable in size to the respective operating conditions, being fitted into said passage duct ( 6 ). Due to the reducible air mass flow that is adaptable to the actual requirements in the space between the turbine rotor wheels, air losses are reduced and efficiency is enhanced.
|
