| 摘要 |
<p>The invention relates to a gas turbine (30) of the axial flow type, comprising a rotor 5 with alternating rows of air-cooled blades (32) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (31) and stator heat shields (36) mounted on a vane carrier (40), whereby the stator coaxially surrounds the rotor to define a hot gas path (39) in between, such that the rows of blades (32) and stator heat shields (36), and the rows of vanes (31) and rotor heat shields are opposite to 10 each other, respectively, and a row of vanes (31) and the next row of blades (32) in the downstream direction define a turbine stage (TS), and whereby the blades (32) are provided with outer blade platforms (34) at their tips. A reduction in cooling air mass flow and leakage in combination with an improved 15 cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing within a turbine stage (TS) means (43-48) to direct cooling air that has already been used to cool, especially the airfoils of the vanes (31) of the turbine stage (TS), into a first cavity (41) located between the outer blade platforms (34) and the opposed stator heat shields (36) for protecting 20 the stator heat shields (36) against the hot gas and for cooling the outer blade platforms (34). (Figure 3) (B) 36 G 41 42 33 37 :1 B 31 Fig.3 TS</p> |
