| 摘要 |
<p>A cooling system for a gas turbine engine which turbine engine includes a compressor unit (1, 2), a combustion chamber (3) and a turbine (4), the cooling system comprising discontinuous cooling by passing at least some of the blades of said turbine alternately through a hot flux from the combustion chamber (3) and a cold flux that does not pass through the combustion chamber with the hot and cold fluxes being separated by partitions at the upstream and downstream ends of the path of the cold flux through the turbine, in conjunction with continuous cooling by circulating air (A) along ducts located inside at least some of the blades of said turbine. <IMAGE></p> |
