| 摘要 |
An insertable impingement rib assembly inside of a turbine vane. The turbine vane has an airfoil portion with a leading edge and a trailing edge. The turbine vane has an inner diameter platform and an outer diameter platform. A guide channel is located in the airfoil portion of the turbine vane. The guide channel has an insertion point, a leading edge guide rail rib, a trailing edge guide rail rib, and a plurality of apertures therethrough. An impingement rib is insertable into the guide channel.
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