| 摘要 |
<p>A blade for a gas turbine comprises: a blade part with a streamlined cross section, which has a leading edge and a trailing edge; a support part which has inlets allowing compressed air to flow in from the outside and which supports one end of the blade part; and a plurality of meandering flow passages one end of which is connected to each inlet and which is extended in parallel inside the blade part to allow the compressed air flowing in through the inlets to pass through. The purpose of the present invention is to provide a blade for a gas turbine, which has improved cooling efficiency, minimizes the pressure loss of compressed air used for cooling the blade, and uniformly cools the entire area of the blade.</p> |
