| 摘要 |
1,120,694. Turbine blades. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. July 12, 1966 [Aug. 2, 1965; June 23, 1966], No.31196/66. Heading F1T. A gas turbine blade 1 mounted on a rotor 3 has internal sealed passages 6, 7 containing a liquid coolant, and passages 2a, 2b adjacent the leading and trailing edges, respectively, supplied with air from the engine compressor by way of the rotor interior, the air exhausting from passages 2a, 2b through orifices 8a, 8b to flow over the exterior of the blade working surfaces. The liquid coolant may be water or a sodiumpotassium eutectic which is liquid at both ambient and turbine operating temperatures. Orifices 8a, 8b may be replaced by porous wall sections. Ribs 5 on the blade root 4 assist the cooling. |
