METHOD FOR COOLING HEAT-STRESSED STRUCTURAL ELEMENTS OF JET-ENGINES,AN APPARATUS FOR THE IMPLEMENTATION OF THE SAID METHOD,AND A DESIGN FOR HEAT-STRESSED BLADES

摘要

PCT No. PCT/EP87/00029 Sec. 371 Date Nov. 18, 1987 Sec. 102(e) Date Nov. 18, 1987 PCT Filed Jan. 23, 1987 PCT Pub. No. WO87/04776 PCT Pub. Date Aug. 13, 1987.Cooling air flows over the inner wall of the blade, and emerges through small orifices provided in the blade jacket in the region of the boundary layer. The cooling air is admitted tangentially into an eddy tube provided with a closure and with a throttle in the region of the latter. The cooling air flow, which is cooled after flowing through the closure is fed into the blades and, after passing over the inner wall of the blade jacket, escapes from each blade in the region of the boundary layer. The heated air flow which escapes from the throttle is evacuated from the blade region. This airflow can be mixed with the cooling air or be introduced into the main gas flow.