| 摘要 |
<p>The present invention provides a blade or a vane component for a turbomachine. The component comprises an inner space (10) between two opposite inner walls (11,12) of the component, a plurality of ribs (21,22) projecting from the two opposite inner walls (11,12) forming a plurality of channels (20) on each of the two opposite inner walls (11,12) to guide the cooling fluid towards the trailing edge (14). The inner space (10) is divided into a leading section (30) towards the leading edge (13) of the component and a trailing section (31) towards the trailing edge (14) of the component, wherein the ribs (21, 22) are arranged in the leading section (30) and a plurality of pin-fins (26) projecting from the two opposite inner walls (11, 12) are arranged in the trailing section (31) in a discrete manner.</p> |
