GAS-TURBINE ENGINE COMPRESSOR FAIRING Russian patent published in 2004 - IPC

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: invention relates to intake heated fairings. Proposed fairing consists of main and heated parts, the latter includes outer and inner shells and slot space for heat carrier. Nozzle is installed coaxially with compressor at slot space inlet. Radial ribs with clearance relative to outer shell are made on inner shell in slot space of heated part. Ratio of heights of slot space at its inlet and outlet is 1.2-3. Ratio of outer diameter of main part of fairing to outer diameter of heated part is 1.2-1.6. Ratio of outer diameter of heated part of fairing to diameter of nozzle is 20-40.

EFFECT: improved efficiency and reliability of gas-turbine engine owing to heating of external surface of fairing.

2 dwg