| 摘要 |
<p>A turbine engine nozzle assembly has an upstream flap assembly having a main flap (226) and a liner (228), a cooling passageway formed between the main flap (226) and liner (228). A downstream flap (26) is pivotally coupled to the upstream flap assembly for relative rotation about a hinge axis (H). The liner (228) has a trailing end (234) spaced upstream from a trailing end of the main flap (226) by at least 40% of a length (LF) of the main flap (226).
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