| 摘要 |
FIELD: mechanical engineering. SUBSTANCE: proposed gas turbine engine is provided with deflector on disk of turbine first stage, with air space in between being connected with cooled blade and interdisk air space. Interdisk air space is connected at outlet with air space between deflector and disk of second stage through jet ring with holes, and through ring slot jet, with interturbine seal and rotor of low-pressure turbine. EFFECT: improved reliability of gas turbine engine by provision of steady air flow rate for cooling turbine blade. 4 dwg |
