Invention Grant
US08011879B2 Transition channel between two turbine stages 有权
两台涡轮级之间的过渡通道

Transition channel between two turbine stages
Abstract:
A transition channel between a first turbine section and a second turbine section for a gas turbine engine is disclosed. The channel includes a first radially external annular wall including ring sector elements housed inside an annular ring and orifices for injecting a fluid into the channel in order to re-energize the boundary layer thereof, a second radially internal annular wall, and a fluid supply device arranged between the space outside the ring and the injection orifices.
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