GAS TURBINE ENGINE Russian patent published in 2012 - IPC F02C7/12

Abstract RU 2443882 C1

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises compressor, unloading chamber downstream of compressor and gas turbine nozzle vanes. First nozzle vane has hollow radial rib, cooled and directed to engine axis and made on lower flange on the side of outlet edge. Radial rib inner chamber inlet communicates with unloading chamber downstream of compressor while its outlet is communicated with turbine flow section via perforation in vane lower flange behind its rear edge. Perforation channels are directed along gas flow direction in turbine flow section.

EFFECT: higher reliability of gas turbine.

2 dwg

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RU 2 443 882 C1

Authors

Kuznetsov Valerij Alekseevich

Dates

2012-02-27—Published

2010-08-23—Filed