| 摘要 |
<p>A combustor (20) for a gas turbine engine is provided that includes a support shell (22), a forward liner segment (24), an aft liner segment (24), and a seal member (26). The support shell (22) has an interior surface (28), and exterior surface (30), and a plurality of impingement apertures (40) disposed within the shell (22). The forward liner segment (24) and aft liner segment (24) are attached to the inner surface of the shell (22). The forward liner segment (24) has an edge surface (42) extending between a face surface (28) and a back surface (40), and a seal shoulder (48). The aft liner segment (24) has an edge surface (42) extending between a face surface (38) and a back surface (40), and a seal shoulder (48). The forward liner segment (24) and the aft liner segment (24) are separated from one another by a gap. The seal member (26) is disposed within the gap. At least some of the plurality of impingement apertures (34) disposed within the shell (22) are aligned with the seal member (26) and oriented to direct cooling air to impinge on the seal member (26).
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