| 摘要 |
<p>A gas turbine engine is provided with a means for cooling tips of turbine blades in a hot turbine section of the engine. Inlet air holds are provided in a radially outer wall section of the combustor, just upstream of a turbine nozzle. Cooling air flows through these inlet air holes, into annulus regions protected from combustion gases, and then downstream along a radially outer wall of the turbine. The cooling air forms a film that cools the turbine blade tips in a localized manner that adds to total engine power output.</p> |
