| 摘要 |
<P>PROBLEM TO BE SOLVED: To cool platform regions of turbine rotor blades. <P>SOLUTION: A platform cooling arrangement for a turbine rotor blade 100 has, in operation, a high-pressure coolant region and a low-pressure coolant region. The platform cooling arrangement includes: an airfoil manifold that resides near the junction of the pressure face 106 of an airfoil 102 with the platform 110; a slash face manifold that resides near a pressure side slash face; a high-pressure connector that connects the airfoil manifold to a high-pressure coolant region of the internal cooling passage; a low-pressure connector that connects the slash face manifold to a low-pressure coolant region of the internal cooling passage; cooling apertures that extend from a starting point along the pressure side slash face to a connection with the airfoil manifold, bisecting the slash face manifold therebetween; and a plurality of non-integral plugs. <P>COPYRIGHT: (C)2012,JPO&INPIT |
