| 摘要 |
The present invention relates to a transition channel ( 10 ) between a first turbine section and a second turbine section for a gas turbine engine, comprising a first radially external annular wall ( 102 ), a second radially internal annular wall, the first wall comprising orifices ( 102 C') for injecting a fluid into the channel in order to re-energize the boundary layer thereof. It is characterized in that the first wall ( 102 ) consists of ring sector elements housed inside an annular ring ( 104 ), fluid supply means being arranged between the space ( 110 ) outside the ring and said injection orifices ( 104 ).
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