| 摘要 |
A turbine assembly (10,10a-10f) comprises a hollow aerofoil (12) having a cavity (14) with an impingement tube (16,16a-16f), which is insertable inside the cavity (14) and is used for impingement cooling of the inner surface (18) of the cavity (14), and with a platform (20,20'), arranged at a radial end (22,22') of the hollow aerofoil (12). A cooling chamber (24,24') used for cooling the platform (20,20') is arranged relative to the hollow aerofoil (12) on an opposed side of the platform (20,20') and is limited at a first radial (26) end from the platform (20,20') and at an opposed radial second end (28) from a cover plate (30,30'). The impingement tube (16) has a first section (32,32a-32f) and at least a second section (34,34a-34f). To minimise aerofoil cooling feed temperatures and increase impingement cooling effectiveness the first section (32,32a-32f) of the impingement tube (16,16a-16f) extends in span wise direction (36) completely through the cooling chamber (24,24') from the platform (20,20') to the cover plate (30,30'). |
