| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an apparatus and method for cooling a platform region of a turbine rotor blade. <P>SOLUTION: A configuration of cooling channels through the interior of the turbine rotor blade is disclosed, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which includes a connection with the platform cooling channel, and a second section, which includes a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension. <P>COPYRIGHT: (C)2012,JPO&INPIT |
