| 摘要 |
A turbine airfoil of a gas turbine engine, the airfoil constructed from a spar and shell, in which the spar includes a root with a plurality of spar cooling air supply channels extending toward the tip and having impingement holes formed along the spar to provide impingement cooling to the shell, and the shell includes a plurality of shell return channels extending from the tip toward the root to channel the impingement cooling air to collector cavities located in the root. With a plurality of spar supply channels and shell return channels, a serpentine flow cooling circuit with multi-impingement cooling of the shell is produced. The cooling air supplied to the spar is discharged out exit holes in the trailing edge in one embodiment, or out exit holes and leading edge film cooling holes in a second embodiment. The spar and shell are bonded together using a low pressure and high temperature bonding process that includes thin sheets containing boron. The bonds are formed between the platforms and the joints between the return channels and the supply channels.
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