| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: blade (10), mostly of high pressure turbine of gas turbine engine, includes ribs (50) formed on inner side near rear edge (42). On larger part of rear edge, in zones in which the operating temperature of blades is especially increased, ends of ribs near rear edge are arranged closer to rear edge and/or section of ribs has larger surface area. Grooves (60) are formed between in-series located ribs (50). Air injection holes (41) are made in those grooves. ^ EFFECT: optimisation of blade design in order to provide the required stiffness of rear edge without excess deterioration of aerodynamic characteristics is provided; such optimised blade design provides its increased service life. ^ 6 cl, 5 dwg |
