| 摘要 |
<p>The present invention relates to a turbine assembly (10, 10a) comprising a basically hollow aerofoil (12) and at least an impingement device (14, 14a, 14d), wherein the hollow aerofoil (12) has at least a first side wall (16, 18) extending from a leading edge (20) towards a trailing edge (22) of the hollow aerofoil (12) and at least a cavity (24) in which in an assembled state of the at least one impingement device (14, 14a, 14d) in the hollow aerofoil (12) the at least one impingement device (14, 14a, 14d) is arranged with a predetermined distance in respect to an inner surface (26) of the cavity (24) for impingement cooling of the at least one inner surface (26) and to form a flow channel (28) for a cooling medium (30) extending from the leading edge (20) towards the trailing edge (22). To minimised aerofoil cooling feed temperatures and increase impingement cooling effectiveness the turbine assembly (10, 10a) comprises at least a first blocking element (32, 32b-d; 34, 34a), which is arranged in the flow channel (28) between the at least one impingement device (14, 14a, 14d) and the at least first side wall (16, 18) of the hollow aerofoil (12) for blocking the flow of cooling medium (30) in direction from the leading edge (20) to the trailing edge (22) of the hollow aerofoil (12).</p> |
