| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: double-flow gas turbine engine includes compressor with dummies cavity, combustion chamber, high and low pressure turbine, and heat exchanger. The latter is arranged in external circuit, the inlet of which is interconnected with secondary combustion chamber zone, and outlet is interconnected through control valves to air manifold connected to transit cavities of blades of nozzle assembly of high and low pressure turbine. Transit cavities of blades of nozzle assembly of high pressure turbine are interconnected with swirling assembly of high pressure turbine. External circuit is interconnected through rotary guide vane and channels in rotor disc of low pressure turbine with inner cavities of cooled rotating blades of low pressure turbine, the outlet of which is interconnected through openings made on bandage flange behind radial tooth, with blading part of turbine. Some part of inner cavity of each rotating blade of LP turbine, which is adjacent to inlet edge, is separated with partition from the rest cavity of rotating blade and is interconnected on one side through additional channels in rotor disc of LP turbine, swirling assembly of LP turbine and additional manifold with transit cavity of blades of nozzle assembly of LP turbine, which is arranged on the side of their inlet edges. In each blade of nozzle assembly of LP turbine, the transit cavity is separated with a partition from the rest part of inner cavity and is connected through additional heat exchanger installed in external circuit to dummies cavity of compressor on the other side. Inner cavity of each rotating blade of LP turbine, which is adjacent to inlet edge, through the openings made on bandage flange of rotating blade of LP turbine before radial tooth is interconnected with blading part of the turbine. ^ EFFECT: invention increases the installed cooling air pressure drop of LP turbine, which improves the cooling efficiency. ^ 9 cl, 6 dwg |
