| 摘要 |
<p>A gas turbine engine has a combustion unit (1) whose chamber (2) has an open annular gap (29) surrounded by a burner ring insert (3). The burner ring insert has a lip seal (7) located above a conical ring and flange (9). A flow of cooling air passes between the lip seal (7) and burner insert (9). The cold air passage converges into the gap (29) between the burner (1) and burner insert (3) and the passage is further sealed against the burner chamber (2). Also claimed is a commensurate gas turbine engine.</p> |
